51320 Federal Register / Vol. 81, No. 150 / Thursday, August 4, 2016 / Rules and Regulations 

FIGURE 2 TO PARAGRAPH (g) OF THIS AD—AFFECTED ACTUATORS ON MODEL FALCON 2000EX AIRPLANES— 

Continued 

Model FALCON 2000EX airplane having S/N— With actuator 

P/N— 

And actuator 

S/N— 

710 ........................................................................................................................................................................... 103151–07 

103151–08 

5051 

5053 

714 ........................................................................................................................................................................... 103151–09 

103151–10 

5065 

5067 

(h) Parts Installation Limitation 

As of the effective date of this AD, no 

aileron servo actuator having a P/N and S/N 

listed in figure 1 to paragraph (g) of this AD 

or figure 2 to paragraph (g) of this AD is 

allowed to be installed on any airplane, 

unless the mark ‘‘D1’’ is included on the 

actuator repair placard. 

Note 2 to paragraph (h) of this AD: The 

mark ‘‘D1’’ on an aileron servo actuator 

repair placard indicates that the affected part 

has been refurbished by an approved 

maintenance organization and is qualified as 

a serviceable part. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, ANM–116, 

International Branch, 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; fax 425–227–1139. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Dassault Aviation’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0184, dated 

August 7, 2014, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2016–5594. 

(k) 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) Dassault Service Bulletin F900EX–476, 

Revision 1, dated June 25, 2014. 

(ii) Dassault Service Bulletin F2000EX– 

350, dated April 9, 2014. 

(3) For service information identified in 

this AD, contact Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, NJ 07606; 

telephone 201–440–6700; Internet http://

www.dassaultfalcon.com. 

(4) 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. 

(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 July 21, 

2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–18167 Filed 8–3–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–0466; Directorate 

Identifier 2014–NM–188–AD; Amendment 

39–18604; AD 2016–16–06] 

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 B4–603, B4–605R, 

and B4–622R airplanes; and Model 

A310–304, –324, and –325 airplanes. 

This AD was prompted by a report of a 

crack found on door frame (FR) 73A 

between stringers 24 and 25. This AD 

requires inspections around the rivet 

heads of the seal retainer run-out holes 

at certain frames and corrective actions 

if necessary. We are issuing this AD to 

detect and correct cracking of the door 

frame, which could result in reduced 

structural integrity of the airplane. 

DATES: This AD is effective September 8, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 8, 2016. 

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 Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2016–0466. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

0466; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this 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. 


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Federal Register / Vol. 81, No. 150 / Thursday, August 4, 2016 / Rules and Regulations 51321 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

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– 

603, B4–605R, and B4–622R airplanes; 

and Model A310–304, -324, and -325 

airplanes. The NPRM published in the 

Federal Register on February 18, 2016 

(81 FR 8155) (‘‘the NPRM’’). The NPRM 

was prompted by a report of a crack 

found on door FR 73A between stringers 

24 and 25. The NPRM proposed to 

require inspections around the rivet 

heads of the seal retainer run-out holes 

at certain frames and corrective actions 

if necessary. We are issuing this AD to 

detect and correct cracking of the door 

frame, which could result in reduced 

structural integrity 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 2014– 

0202R1, dated September 19, 2014 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

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

condition for certain Airbus Model 

A300 B4–603, B4–605R, and B4–622R 

airplanes; and Model A310–304, –324, 

and –325 airplanes The MCAI states: 

During the preparation phase for 

conversion of an A300–600 aeroplane from 

passenger to freighter configuration, a crack 

was detected on door frame (FR) 73A, 

between stringer (STRG) 24 and STRG 25. 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France had issued AD 1999–013– 

276R1 to require inspections at FR 73A in 

accordance with the instructions of Airbus 

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

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

new crack was found in an area not covered 

by the existing inspection and is therefore 

addressed by this new [EASA] AD. (DGAC 

France AD 1999–013–276R1 remains in 

place). 

Further investigations identified that, on 

A300–600 aeroplanes, the areas at FR 56A 

and FR 57A have the same design and 

material as at FR 73A. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the airframe. 

For the reasons described above, this 

[EASA] AD requires repetitive [high 

frequency eddy current (HFEC)] inspections 

of the rivet heads of the seal retainer run out 

holes to detect cracks and, depending on 

findings, accomplishment of corrective 

actions [repair]. 

Even though no crack has been identified 

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

measure, the inspection is extended to these 

areas. On A310 aeroplanes, only the area at 

FR 73A needs to be inspected. 

This [EASA] AD is revised to reduce the 

applicability to aeroplanes in post-MOD 

06924 configuration. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

0466. 

Comments 

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 the comment. 

Request To Reduce Compliance Time 

An anonymous commenter asked why 

the NPRM has not yet been enacted. The 

commenter stated that they do not want 

to be on a plane that lacks structural 

integrity because of cracks on the door 

frame. 

ADs are federal regulations that have 

the force and effect of law. In simple 

terms, the Administrative Procedure Act 

(APA), Title 5 of the United States Code 

(5 U.S.C.) § 553, requires all regulatory 

agencies such as the FAA to provide the 

public with notice and time for 

comment prior to issuing a regulation. 

ADs are issued in accordance with the 

public rulemaking procedures of the 

APA, FAA procedures in 14 CFR part 

11, and several other relevant 

regulations. For this AD, we did not 

substantiate that a critical, immediate 

safety of flight problem exists that 

would warrant issuing a rule without 

prior notice or opportunity for public 

comment. We have not changed this AD 

in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comment 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 Service Bulletins 

A300–53–6175 and A310–53–2138, both 

dated May 28, 2014. The service 

information describes procedures for 

doing HFEC inspections around the 

rivet heads of the seal retainer run-out 

holes at certain frame locations on the 

left-hand and right-hand sides. This 

service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 24 

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 

Inspection ............................... 11 work-hours × $85 per hour 

= $935 per inspection cycle.

$0 $935 per inspection cycle ...... $22,440 per inspection cycle. 

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 


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51322 Federal Register / Vol. 81, No. 150 / Thursday, August 4, 2016 / Rules and Regulations 

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 adding 

the following new airworthiness 

directive (AD): 

2016–16–06 Airbus: Amendment 39–18604; 

Docket No. FAA–2016–0466; Directorate 

Identifier 2014–NM–188–AD. 

(a) Effective Date 

This AD is effective September 8, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A300 B4– 

603, A300 B4–605R, A300 B4–622R, A310– 

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

certificated in any category; all manufacturer 

serial numbers (MSNs) in post-modification 

(MOD) 06924 configuration, except MSNs 

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

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

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

partially embodied MOD 06924 by means of 

modification proposal D05902. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of a 

crack found on door frame (FR) 73A between 

stringers 24 and 25. We are issuing this AD 

to detect and correct cracking of the door 

frame, 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) Inspections for Cracking 

At the later of the compliance times 

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

this AD: Do a high frequency eddy current 

(HFEC) inspection for any crack around the 

rivet heads of the seal retainer run-out holes 

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

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

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

RH sides on Model A310 airplanes; in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A310– 

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

Service Bulletin A300–53–6175, dated May 

28, 2014; as applicable. Repeat the HFEC 

inspection thereafter at intervals not to 

exceed 7,500 flight cycles. 

(1) Before the accumulation of 32,000 total 

flight cycles. 

(2) Within 36 months after the effective 

date of this AD, or before the accumulation 

of 36,000 total flight cycles, whichever 

occurs first. 

(h) Corrective Actions 

If any crack is found during any inspection 

required by paragraph (g) of this AD, repair 

before further flight using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (h) of this AD: If 

any service information contains procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2014–0202R1, dated September 19, 2014, for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2016–0466. 

(k) 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 A300–53–6175, 

dated May 28, 2014. 

(ii) Airbus Service Bulletin A310–53–2138, 

dated May 28, 2014. 

(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 Airplane Directorate, 

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 July 21, 

2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–18254 Filed 8–3–16; 8:45 am] 

BILLING CODE 4910–13–P 


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