48906 Federal Register / Vol. 82, No. 203 / Monday, October 23, 2017 / Rules and Regulations 

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 adding 

the following new airworthiness 

directive (AD): 

2017–21–08 Airbus: Amendment 39–19079; 

Docket No. FAA–2017–0628; Product 

Identifier 2016–NM–207–AD. 

(a) Effective Date 

This AD is effective November 27, 2017. 

(b) Affected ADs 

This AD affects AD 2013–13–13, 

Amendment 39–17501 (79 FR 48957, August 

19, 2014) (‘‘AD 2013–13–13’’). 

(c) Applicability 

This AD applies to all Airbus Model A310– 

203, –204, –221, –222, –304, –322, –324, and 

–325 airplanes, certificated in any category, 

all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05. 

(e) Reason 

This AD was prompted by a revision of 

certain airworthiness limitation items (ALI) 

documents, which require more restrictive 

maintenance requirements and airworthiness 

limitations. We are issuing this AD to prevent 

fatigue cracking, damage, or corrosion in 

principal structural elements, which could 

result in reduced structural integrity of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revision of Maintenance or Inspection 

Program 

Within 3 months after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate the 

information specified in paragraphs (g)(1), 

(g)(2), and (g)(3) of this AD. The initial 

compliance times for doing the tasks is at the 

time specified in the service information 

identified in paragraphs (g)(1), (g)(2), and 

(g)(3) of this AD, or within 3 months after the 

effective date of this AD, whichever occurs 

later. 

(1) Airbus A310 Airworthiness Limitations 

Section (ALS), Part 2, ‘‘Damage Tolerant 

Airworthiness Limitation Items (DT–ALI),’’ 

Revision 01, dated August 7, 2015. 

(2) Airbus A310 Airworthiness Limitations 

Section (ALS), Part 2, ‘‘Damage Tolerant 

Airworthiness Limitation Items (DT–ALI),’’ 

Variation 1.1, dated January 25, 2016. 

(3) Airbus A310 Airworthiness Limitations 

Section (ALS), Part 2, ‘‘Damage Tolerant 

Airworthiness Limitation Items (DT–ALI),’’ 

Variation 1.2, dated July 22, 2016. 

(h) No Alternative Actions or Intervals 

After the maintenance or inspection 

program has been revised as required by 

paragraph (g) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions and/or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (j)(1) of 

this AD. 

(i) Terminating Action for AD 2013–13–13 

Accomplishing the actions required by this 

AD terminates all requirements of AD 2013– 

13–13 for that airplane only. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(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 (k)(2) of this AD. Information may 

be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Section, 

Transport Standards Branch, FAA; or the 

European Aviation Safety Agency (EASA); or 

Airbus’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2016–0217, dated November 2, 2016, 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–2017–0628. 

(2) For more information about this AD, 

contact Dan Rodina, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone 425– 

227–2125; fax 425–227–1149. 

(l) 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. 

(i) Airbus A310 Airworthiness Limitations 

Section (ALS), Part 2, ‘‘Damage Tolerant 

Airworthiness Limitation Items (DT–ALI),’’ 

Revision 01, dated August 7, 2015. 

(ii) Airbus A310 Airworthiness Limitations 

Section (ALS), Part 2, ‘‘Damage Tolerant 

Airworthiness Limitation Items (DT–ALI),’’ 

Variation 1.1, dated January 25, 2016. 

(iii) Airbus A310 Airworthiness 

Limitations Section (ALS), Part 2, ‘‘Damage 

Tolerant Airworthiness Limitation Items 

(DT–ALI),’’ Variation 1.2, dated July 22, 

2016. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

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

(4) You may view this service information 

at the FAA, Transport Standards Branch, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) 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 October 

11, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–22710 Filed 10–20–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0497; Product 

Identifier 2016–NM–209–AD; Amendment 

39–19078; AD 2017–21–07] 

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 all 

Airbus Model A300 series airplanes. 

This AD was prompted by a report of 

reduction of the de-icing performance of 

the pitot probe over time that could 

remain hidden to the flight crew. This 


jstallworth on DSKBBY8HB2PROD with RULES
Federal Register / Vol. 82, No. 203 / Monday, October 23, 2017 / Rules and Regulations 48907 

AD requires repetitive detailed 

inspections of the pitot probe heater 

insulation resistance, and replacement 

of the pitot probe heater if necessary. 

We are issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective November 

27, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 27, 2017. 

ADDRESSES: For service information 

identified in this final rule, 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. You may view this 

referenced service information at the 

FAA, Transport Standards Branch, 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–2017– 

0497. 

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–2017– 

0497; 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 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: Dan 

Rodina, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–227–2125; 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 all Airbus Model A300 series 

airplanes. The NPRM published in the 

Federal Register on May 30, 2017 (82 

FR 24601) (‘‘the NPRM’’). The NPRM 

was prompted by a report of reduction 

of the de-icing performance of the pitot 

probe over time that could remain 

hidden to the flight crew. The NPRM 

proposed to require repetitive detailed 

inspections of the pitot probe heater 

insulation resistance, and replacement 

of the pitot probe heater if necessary. 

We are issuing this AD to ensure 

nominal de-icing performance of the 

pitot probe in order to prevent 

unreliable airspeed indications, which 

could result in reduced control of the 

airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2016–0248, 

dated December 15, 2016 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus Model A300 series 

airplanes. The MCAI states: 

An operator reported a reduction of the 

deicing performance of the pitot probe over 

the time. Pitot probes are heated to prevent 

ice accretion. De-icing performances of the 

Pitot probe might be reduced if Pitot probe 

heater degrades over time. Investigation 

results highlighted that the magnitude of deicing performance reduction depended on 

how much the [pitot probe] heater is 

degraded. This degradation could remain 

hidden to the crew. 

Pitot probes heater degradation, if not 

detected and corrected, could lead to 

unreliable airspeed indications, possibly 

resulting in reduced control of the aeroplane. 

To ensure nominal de-icing performances 

of the Pitot probe, Airbus developed an 

inspection process to check the pitot [probe] 

heater performance, and published Service 

Bulletin (SB) A300–34–0185 to provide the 

necessary instructions to operators. 

For the reasons described above, this 

[EASA] AD requires repetitive detailed 

inspections (DET) of the pitot [probe] heater, 

and, depending on findings, replacement 

with a serviceable one. 

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–2017– 

0497. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Reduce the Maximum 

Possible Initial Compliance Time 

The Air Line Pilots Association, 

International (ALPA) expressed its 

partial support for the NPRM. ALPA 

requested that we change the 

introductory text of paragraph (h) of the 

proposed AD from ‘‘. . . whichever 

occurs later . . .’’ to ‘‘. . . whichever 

occurs first . . .’’ ALPA is concerned 

that a possible duration of 30 months to 

comply with the initial inspection 

requirement of the NPRM is too long 

and could adversely affect safety. ALPA 

also mentioned that they preferred that 

no more than 24 months pass between 

inspections. 

We do not agree with the commenter’s 

request to shorten the compliance time. 

After considering the available 

information, we have determined that 

the compliance time, as proposed, 

represents an appropriate interval of 

time in which the required actions can 

be performed in a timely manner within 

the affected fleet, while still maintaining 

an adequate level of safety. In 

developing an appropriate compliance 

time, we considered the safety 

implications, parts availability, and 

normal maintenance schedules for 

timely accomplishment of the detailed 

inspections. The proposed compliance 

time corresponds with the compliance 

times specified in the MCAI. 

Additionally, the affected airplanes are 

currently in storage. To reduce the 

compliance time of the proposed AD 

would necessitate (under the provisions 

of the Administrative Procedure Act) 

reissuing the notice, reopening the 

period for public comment, considering 

additional comments subsequently 

received, and eventually issuing a final 

rule. That process would delay issuance 

of the final rule. In light of this, and in 

consideration of the amount of time that 

has already elapsed since issuance of 

the original notice, we have determined 

that further delay of this AD is not 

appropriate. We have not changed this 

AD in this regard. 

Request To Reduce Compliance Time 

for Reporting 

Airbus recommended that we reduce 

the compliance time for reporting from 

30 days to 10 days (after the effective 

date of this AD) for inspections with 

findings. No further justification was 

provided. 

We do not agree with the commenter’s 

request to reduce the compliance time 

for reporting. After considering the 

available information, we have 

determined that the compliance time for 

reporting findings, as proposed, 

represents an appropriate interval of 

time in which the required actions can 

be performed in a timely manner within 

the affected fleet, while still maintaining 

an adequate level of safety. To reduce 

the reporting compliance time of this 

AD would, as mentioned previouly, 

necessitate reissuing the notice, 

reopening the period for public 

comment, considering additional 

comments subsequently received, and 


jstallworth on DSKBBY8HB2PROD with RULES
48908 Federal Register / Vol. 82, No. 203 / Monday, October 23, 2017 / Rules and Regulations 

eventually issuing a final rule. In light 

of this, we have determined that the 30- 

day compliance time for reporting is 

appropriate. 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 AD 

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 

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 A300–34–0185, Revision 00, 

dated August 29, 2016. The service 

information describes procedures for 

repetitive detailed inspections of the 

pitot probe heater insulation resistance 

and replacement of the pitot probe 

heater. 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 5 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Repetitive inspection ..... 5 work-hours × $85 per hour = $425 per inspection cycle.$0 $425 per inspection 

cycle.

$2,125 per inspection 

cycle. 

Reporting ....................... 1 work hour × $85 per hour = $85 per inspection cycle.$0 $85 per inspection 

cycle.

$425 per inspection 

cycle. 

We estimate the following costs to do 

any necessary replacement that will be 

required based on the results of the 

required inspection. We have no way of 

determining the number of aircraft that 

might need this replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement .................................... 3 work-hours × $85 per hour = $255 ........................................................ $9,015 $9,270 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

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 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, 


jstallworth on DSKBBY8HB2PROD with RULES
Federal Register / Vol. 82, No. 203 / Monday, October 23, 2017 / Rules and Regulations 48909 

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 adding 

the following new airworthiness 

directive (AD): 

2017–21–07 Airbus: Amendment 39–19078; 

Docket No. FAA–2017–0497; Product 

Identifier 2016–NM–209–AD. 

(a) Effective Date 

This AD is effective November 27, 2017. 

(b) Effective Date 

None. 

(c) Applicability 

This AD applies to Airbus Model A300 B2– 

1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, 

and B4–203 airplanes, certificated in any 

category, all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 34, Navigation. 

(e) Reason 

This AD was prompted by a report of 

reduction of the de-icing performance of the 

pitot probe over time that could remain 

hidden to the flight crew. We are issuing this 

AD to ensure nominal de-icing performance 

of the pitot probe in order to prevent 

unreliable airspeed indications, which could 

result in reduced control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definition of Pitot Probes 

For the purpose of this AD, affected pitot 

probes are the First Officer’s Pitot Probe 

40DA, Captain’s Pitot Probe 41DA, and 

Standby Pitot Probe 42DA. 

(h) Repetitive Inspections 

At the time specified in paragraph (h)(1) or 

(h)(2) of this AD, whichever occurs later, do 

a detailed inspection of the pitot probe heater 

insulation resistance on each affected pitot 

probe, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–34–0185, Revision 00, 

dated August 29, 2016. Repeat the inspection 

thereafter at intervals not to exceed 24 

months. 

(1) Within 24 months since the last 

detailed inspection of the pitot probe heater 

insulation resistance, as specified in Airbus 

A300 Aircraft Maintenance Manual (AMM), 

Task 30–31–00, Insulation Test of Pitot 

Heater Resistance. 

(2) Within 6 months after the effective date 

of this AD. 

(i) Corrective Action 

If, during any detailed inspection as 

required by paragraph (h) of this AD, any 

pitot probe fails the test, as specified in the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–34–0185, Revision 00, 

dated August 29, 2016, before further flight, 

replace the affected pitot probe with a 

serviceable (new or inspected as required by 

this AD) pitot probe, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–34–0185, Revision 00, 

dated August 29, 2016. Replacement of pitot 

probes, as required by this paragraph, does 

not constitute terminating action for the 

repetitive inspections required by paragraph 

(h) of this AD. 

(j) Reporting 

At the applicable times required by 

paragraph (j)(1) or (j)(2) of this AD: Submit 

a report of the findings (both positive and 

negative) of each inspection required by 

paragraph (h) of this AD, as specified in the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–34–0185, Revision 00, 

dated August 29, 2016, to Airbus Service 

Bulletin Reporting Online Application on 

Airbus World (https://w3.airbus.com/). 

(1) For inspections done before the 

effective date of this AD: Within 30 days after 

the effective date of this AD. 

(2) For inspections done on or after the 

effective date of this AD: Within 30 days after 

accomplishing each inspection required by 

paragraph (h) 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 

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 (l)(2) of this AD. Information may 

be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Section, 

Transport Standards Branch, FAA; or the 

European Aviation Safety Agency (EASA); or 

Airbus’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(4) Required for Compliance (RC): Except 

as required by paragraph (j) of this AD: If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2016–0248, dated December 15, 2016, 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–2017–0497. 

(2) For more information about this AD, 

contact Dan Rodina, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone: 425– 

227–2125; fax: 425–227–1149. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (m)(3) and (m)(4) of this AD. 

(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. 

(i) Airbus Service Bulletin A300–34–0185, 

Revision 00, dated August 29, 2016. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone: +33 5 61 93 36 96; fax: +33 5 61 

93 44 51; email: account.airworth-eas@

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

(4) You may view this service information 

at the FAA, Transport Standards Branch, 

1601 Lind Avenue SW., Renton, WA. For 


jstallworth on DSKBBY8HB2PROD with RULES
48910 Federal Register / Vol. 82, No. 203 / Monday, October 23, 2017 / Rules and Regulations 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) 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 October 

10, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–22709 Filed 10–20–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0480; Product 

Identifier 2016–NM–204–AD; Amendment 

39–19073; AD 2017–21–02] 

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 A300 B4–600, B4–600R, 

and F4–600R series airplanes, and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes); and Model 

A310 series airplanes. This AD was 

prompted by a report of cracking in the 

door sill area of the aft cargo door. This 

AD requires repetitive inspections of the 

aft cargo door lower torsion box area, 

and corrective actions if necessary. We 

are issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective November 

27, 2017. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 27, 2017. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus SAS, Airworthiness Office— 

EAW, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone 

+33 5 61 93 36 96; fax +33 5 61 93 44 

51; email account.airworth-eas@

airbus.com; Internet http://

www.airbus.com. You may view this 

referenced service information at the 

FAA, Transport Standards Branch, 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–2017– 

0480. 

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–2017– 

0480; 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 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: Dan 

Rodina, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; 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 A300 B4– 

600, B4–600R, and F4–600R series 

airplanes, and Model A300 C4–605R 

Variant F airplanes (collectively called 

Model A300–600 series airplanes); and 

Model A310 series airplanes. The NPRM 

published in the Federal Register on 

May 22, 2017 (82 FR 23166) (‘‘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 2016–0241, dated December 6, 

2016 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Airbus 

Model A300 B4–600, B4–600R, and F4– 

600R series airplanes, and Model A300 

C4–605R Variant F airplanes 

(collectively called Model A300–600 

series airplanes); and Model A310 series 

airplanes. The MCAI states: 

Cracks were found on in-service aeroplane 

post mod 5438 in the door sill area, from 

frame (FR) 60 to FR63, including the sill 

beam flag, lock fitting, door sill web and 

torsion door panel. Two previous cases with 

less crack extent were also reported. 

This condition, if not detected and 

corrected, could lead to reduced structural 

integrity of the aeroplane. 

To address this unsafe condition, Airbus 

published Inspection Service Bulletin (SB) 

A310–53–2139 and SB A300–53–6179 to 

provide inspection instructions for the 

affected areas. Airbus published also Airbus 

SB A310–53–2141 and SB A300–53–6181 to 

provide modification instructions. 

Further analysis showed that aeroplanes 

pre-mod 5438, for which one or several lock 

fittings have been replaced by post mod 

10319 lock fittings, could also be affected. 

Airbus published SB A310–53–2143 and SB 

A300–53–6185 to provide inspection 

instructions. 

For the reason described above, this 

[EASA] AD requires repetitive Special 

Detailed Inspections (SDI) of the aft cargo 

door lower torsion box area and, depending 

on findings, accomplishment of applicable 

corrective action(s). 

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–2017– 

0480. 

Comment 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM and the FAA’s 

response to that comment. 

Request To Clarify Terminating Action 

United Parcel Service (UPS) requested 

that the terminating action specified in 

paragraph (i) of the proposed AD be 

clarified to specify that the repair of a 

damaged fitting is terminating action for 

the repetitive inspections specified in 

paragraph (g) of the proposed AD for the 

repaired fitting location only. The 

commenter stated that this clarification 

would mitigate premature termination 

of repetitive inspections of the aft cargo 

door lower torsion box area. 

We agree with the commenter’s 

request for the reasons provided by the 

commenter. We have revised paragraph 

(i) of this AD to specify that repair of a 

lock fitting as required by paragraph (h) 

of this AD constitutes terminating action 

for the repetitive inspections required 

by paragraph (g) of this AD for the 

repaired fitting location only. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

with the change described previously 

and minor editorial changes. We have 

determined that these minor changes: 


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