81_FR_51470 81 FR 51320 - Airworthiness Directives; Airbus Airplanes

81 FR 51320 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 150 (August 4, 2016)

Page Range51320-51322
FR Document2016-18254

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.

Federal Register, Volume 81 Issue 150 (Thursday, August 4, 2016) 
[Federal Register Volume 81, Number 150 (Thursday, August 4, 2016)]
[Rules and Regulations]
[Pages 51320-51322]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-18254]


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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 [email protected]; 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.

[[Page 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 G[eacute]n[eacute]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.) Sec.  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
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                    Labor cost         Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection......................  11 work-hours x $85              $0   $935 per inspection  $22,440 per
                                   per hour = $935                       cycle.               inspection cycle.
                                   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

[[Page 51322]]

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

0
1. The authority citation for part 39 continues to read as follows:

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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: [email protected]. 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 [email protected]; 
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/ibr-locations.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

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 With actuator And actuator Model FALCON 2000EX airplane having S/N— P/N— S/N— 710 ........................................................................................................................................................................... 103151–07 5051 103151–08 5053 714 ........................................................................................................................................................................... 103151–09 5065 103151–10 5067 (h) Parts Installation Limitation (k) Material Incorporated by Reference Airbus Model A300 B4–603, B4–605R, As of the effective date of this AD, no (1) The Director of the Federal Register and B4–622R airplanes; and Model aileron servo actuator having a P/N and S/N approved the incorporation by reference A310–304, –324, and –325 airplanes. listed in figure 1 to paragraph (g) of this AD (IBR) of the service information listed in this This AD was prompted by a report of a or figure 2 to paragraph (g) of this AD is paragraph under 5 U.S.C. 552(a) and 1 CFR crack found on door frame (FR) 73A allowed to be installed on any airplane, part 51. between stringers 24 and 25. This AD unless the mark ‘‘D1’’ is included on the (2) You must use this service information as applicable to do the actions required by requires inspections around the rivet actuator repair placard. this AD, unless this AD specifies otherwise. heads of the seal retainer run-out holes Note 2 to paragraph (h) of this AD: The (i) Dassault Service Bulletin F900EX–476, at certain frames and corrective actions mark ‘‘D1’’ on an aileron servo actuator repair placard indicates that the affected part Revision 1, dated June 25, 2014. if necessary. We are issuing this AD to has been refurbished by an approved (ii) Dassault Service Bulletin F2000EX– detect and correct cracking of the door maintenance organization and is qualified as 350, dated April 9, 2014. frame, which could result in reduced a serviceable part. (3) For service information identified in structural integrity of the airplane. this AD, contact Dassault Falcon Jet, P.O. Box DATES: This AD is effective September 8, (i) Other FAA AD Provisions 2000, South Hackensack, NJ 07606; telephone 201–440–6700; Internet http:// 2016. The following provisions also apply to this The Director of the Federal Register www.dassaultfalcon.com. AD: approved the incorporation by reference (4) You may view this service information (1) Alternative Methods of Compliance of certain publications listed in this AD at the FAA, Transport Airplane Directorate, (AMOCs): The Manager, ANM–116, International Branch, Transport Airplane 1601 Lind Avenue SW., Renton, WA. For as of September 8, 2016. information on the availability of this ADDRESSES: For service information Directorate, FAA, has the authority to material at the FAA, call 425–227–1221. identified in this final rule, contact approve AMOCs for this AD, if requested (5) You may view this service information using the procedures found in 14 CFR 39.19. Airbus SAS, Airworthiness Office— that is incorporated by reference at the In accordance with 14 CFR 39.19, send your EAW, 1 Rond Point Maurice Bellonte, National Archives and Records request to your principal inspector or local 31707 Blagnac Cedex, France; telephone Administration (NARA). For information on Flight Standards District Office, as +33 5 61 93 36 96; fax +33 5 61 93 44 the availability of this material at NARA, call appropriate. If sending information directly 202–741–6030, or go to: http:// 51; email account.airworth-eas@ to the International Branch, send it to ATTN: Tom Rodriguez, Aerospace Engineer, www.archives.gov/federal-register/cfr/ibr- airbus.com; Internet http:// locations.html. www.airbus.com. You may view this International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Issued in Renton, Washington, on July 21, referenced service information at the Avenue SW., Renton, WA 98057–3356; 2016. FAA, Transport Airplane Directorate, telephone 425–227–1137; fax 425–227–1139. Michael Kaszycki, 1601 Lind Avenue SW., Renton, WA. Information may be emailed to: 9-ANM-116- Acting Manager, Transport Airplane For information on the availability of AMOC-REQUESTS@faa.gov. Before using this material at the FAA, call 425–227– Directorate, Aircraft Certification Service. any approved AMOC, notify your appropriate 1221. It is also available on the Internet principal inspector, or lacking a principal [FR Doc. 2016–18167 Filed 8–3–16; 8:45 am] inspector, the manager of the local flight BILLING CODE 4910–13–P at http://www.regulations.gov by standards district office/certificate holding searching for and locating Docket No. district office. The AMOC approval letter FAA–2016–0466. must specifically reference this AD. DEPARTMENT OF TRANSPORTATION Examining the AD Docket (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective Federal Aviation Administration You may examine the AD docket on actions from a manufacturer, the action must the Internet at http:// be accomplished using a method approved 14 CFR Part 39 www.regulations.gov by searching for by the Manager, International Branch, ANM– and locating Docket No. FAA–2016– 116, Transport Airplane Directorate, FAA; or [Docket No. FAA–2016–0466; Directorate 0466; or in person at the Docket the European Aviation Safety Agency Identifier 2014–NM–188–AD; Amendment Management Facility between 9 a.m. (EASA); or Dassault Aviation’s EASA Design 39–18604; AD 2016–16–06] Organization Approval (DOA). If approved by and 5 p.m., Monday through Friday, the DOA, the approval must include the RIN 2120–AA64 except Federal holidays. The AD docket DOA-authorized signature. contains this AD, the regulatory Airworthiness Directives; Airbus evaluation, any comments received, and (j) Related Information Airplanes other information. The street address for Refer to Mandatory Continuing the Docket Office (telephone 800–647– AGENCY: Federal Aviation ehiers on DSK5VPTVN1PROD with RULES Airworthiness Information (MCAI) EASA 5527) is Docket Management Facility, Airworthiness Directive 2014–0184, dated Administration (FAA), Department of August 7, 2014, for related information. This Transportation (DOT). U.S. Department of Transportation, MCAI may be found in the AD docket on the ACTION: Final rule. Docket Operations, M–30, West Internet at http://www.regulations.gov by Building Ground Floor, Room W12–140, searching for and locating Docket No. FAA– SUMMARY: We are adopting a new 1200 New Jersey Avenue SE., 2016–5594. airworthiness directive (AD) for certain Washington, DC 20590. VerDate Sep<11>2014 13:37 Aug 03, 2016 Jkt 238001 PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 E:\FR\FM\04AUR1.SGM 04AUR1

Federal Register / Vol. 81, No. 150 / Thursday, August 4, 2016 / Rules and Regulations 51321 FOR FURTHER INFORMATION CONTACT: Dan A300–53–6116, as applicable. However, the public with notice and time for Rodina, Aerospace Engineer, new crack was found in an area not covered comment prior to issuing a regulation. International Branch, ANM–116, by the existing inspection and is therefore ADs are issued in accordance with the addressed by this new [EASA] AD. (DGAC Transport Airplane Directorate, FAA, France AD 1999–013–276R1 remains in public rulemaking procedures of the 1601 Lind Avenue SW., Renton, WA place). APA, FAA procedures in 14 CFR part 98057–3356; telephone 425–227–2125; Further investigations identified that, on 11, and several other relevant fax 425–227–1149. A300–600 aeroplanes, the areas at FR 56A regulations. For this AD, we did not SUPPLEMENTARY INFORMATION: and FR 57A have the same design and substantiate that a critical, immediate material as at FR 73A. safety of flight problem exists that Discussion This condition, if not detected and would warrant issuing a rule without corrected, could affect the structural integrity We issued a notice of proposed prior notice or opportunity for public of the airframe. rulemaking (NPRM) to amend 14 CFR For the reasons described above, this comment. We have not changed this AD part 39 by adding an AD that would [EASA] AD requires repetitive [high in this regard. apply to certain Airbus Model A300 B4– frequency eddy current (HFEC)] inspections Conclusion 603, B4–605R, and B4–622R airplanes; of the rivet heads of the seal retainer run out and Model A310–304, -324, and -325 holes to detect cracks and, depending on We reviewed the relevant data, airplanes. The NPRM published in the findings, accomplishment of corrective considered the comment received, and actions [repair]. Federal Register on February 18, 2016 determined that air safety and the Even though no crack has been identified (81 FR 8155) (‘‘the NPRM’’). The NPRM at FR 56A and FR 57A, as a preventive public interest require adopting this AD was prompted by a report of a crack measure, the inspection is extended to these as proposed except for minor editorial found on door FR 73A between stringers areas. On A310 aeroplanes, only the area at changes. We have determined that these 24 and 25. The NPRM proposed to FR 73A needs to be inspected. minor changes: require inspections around the rivet This [EASA] AD is revised to reduce the • Are consistent with the intent that heads of the seal retainer run-out holes applicability to aeroplanes in post-MOD was proposed in the NPRM for 06924 configuration. at certain frames and corrective actions correcting the unsafe condition; and if necessary. We are issuing this AD to You may examine the MCAI in the • Do not add any additional burden detect and correct cracking of the door AD docket on the Internet at http:// upon the public than was already frame, which could result in reduced www.regulations.gov by searching for proposed in the NPRM. structural integrity of the airplane. and locating Docket No. FAA–2016– The European Aviation Safety Agency 0466. Related Service Information Under 1 (EASA), which is the Technical Agent CFR Part 51 Comments for the Member States of the European Airbus has issued Service Bulletins Union, has issued EASA AD 2014– We gave the public the opportunity to participate in developing this AD. The A300–53–6175 and A310–53–2138, both 0202R1, dated September 19, 2014 dated May 28, 2014. The service (referred to after this as the Mandatory following presents the comment received on the NPRM and the FAA’s information describes procedures for Continuing Airworthiness Information, doing HFEC inspections around the or ‘‘the MCAI’’), to correct an unsafe response to the comment. rivet heads of the seal retainer run-out condition for certain Airbus Model Request To Reduce Compliance Time holes at certain frame locations on the A300 B4–603, B4–605R, and B4–622R left-hand and right-hand sides. This An anonymous commenter asked why airplanes; and Model A310–304, –324, service information is reasonably the NPRM has not yet been enacted. The and –325 airplanes The MCAI states: available because the interested parties commenter stated that they do not want During the preparation phase for to be on a plane that lacks structural have access to it through their normal conversion of an A300–600 aeroplane from integrity because of cracks on the door course of business or by the means passenger to freighter configuration, a crack frame. identified in the ADDRESSES section. was detected on door frame (FR) 73A, ADs are federal regulations that have between stringer (STRG) 24 and STRG 25. Costs of Compliance DGAC [Direction Générale de l’Aviation the force and effect of law. In simple Civile] France had issued AD 1999–013– terms, the Administrative Procedure Act We estimate that this AD affects 24 276R1 to require inspections at FR 73A in (APA), Title 5 of the United States Code airplanes of U.S. registry. accordance with the instructions of Airbus (5 U.S.C.) § 553, requires all regulatory We estimate the following costs to Service Bulletin (SB) A310–53–2107 or SB agencies such as the FAA to provide the 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 $0 $935 per inspection cycle ...... $22,440 per inspection cycle. = $935 per inspection cycle. We have received no definitive data section 106, describes the authority of section, Congress charges the FAA with that would enable us to provide cost the FAA Administrator. ‘‘Subtitle VII: promoting safe flight of civil aircraft in estimates for the on-condition actions Aviation Programs,’’ describes in more air commerce by prescribing regulations ehiers on DSK5VPTVN1PROD with RULES specified in this AD. detail the scope of the Agency’s for practices, methods, and procedures authority. the Administrator finds necessary for Authority for this Rulemaking We are issuing this rulemaking under safety in air commerce. This regulation Title 49 of the United States Code the authority described in ‘‘Subtitle VII, is within the scope of that authority specifies the FAA’s authority to issue Part A, Subpart III, Section 44701: because it addresses an unsafe condition rules on aviation safety. Subtitle I, General requirements.’’ Under that that is likely to exist or develop on VerDate Sep<11>2014 13:37 Aug 03, 2016 Jkt 238001 PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 E:\FR\FM\04AUR1.SGM 04AUR1

51322 Federal Register / Vol. 81, No. 150 / Thursday, August 4, 2016 / Rules and Regulations products identified in this rulemaking (d) Subject (2) Contacting the Manufacturer: For any action. Air Transport Association (ATA) of requirement in this AD to obtain corrective America Code 53, Fuselage. actions from a manufacturer, the action must Regulatory Findings be accomplished using a method approved (e) Reason by the Manager, International Branch, ANM– We determined that this AD will not This AD was prompted by a report of a 116, Transport Airplane Directorate, FAA; have federalism implications under EASA; or Airbus’s EASA DOA. If approved Executive Order 13132. This AD will crack found on door frame (FR) 73A between stringers 24 and 25. We are issuing this AD by the DOA, the approval must include the not have a substantial direct effect on to detect and correct cracking of the door DOA-authorized signature. the States, on the relationship between frame, which could result in reduced (3) Required for Compliance (RC): Except the national government and the States, structural integrity of the airplane. as required by paragraph (h) of this AD: If or on the distribution of power and any service information contains procedures (f) Compliance or tests that are identified as RC, those responsibilities among the various levels of government. Comply with this AD within the procedures and tests must be done to comply compliance times specified, unless already with this AD; any procedures or tests that are For the reasons discussed above, I not identified as RC are recommended. Those certify that this AD: done. procedures and tests that are not identified 1. Is not a ‘‘significant regulatory (g) Inspections for Cracking as RC may be deviated from using accepted action’’ under Executive Order 12866; At the later of the compliance times methods in accordance with the operator’s 2. Is not a ‘‘significant rule’’ under the specified in paragraphs (g)(1) and (g)(2) of maintenance or inspection program without DOT Regulatory Policies and Procedures this AD: Do a high frequency eddy current obtaining approval of an AMOC, provided (44 FR 11034, February 26, 1979); (HFEC) inspection for any crack around the the procedures and tests identified as RC can 3. Will not affect intrastate aviation in rivet heads of the seal retainer run-out holes be done and the airplane can be put back in Alaska; and at FR 56A, FR 57A, and FR 73A, left-hand an airworthy condition. Any substitutions or 4. Will not have a significant (LH) and right-hand (RH) sides on Model changes to procedures or tests identified as economic impact, positive or negative, A300–600 airplanes; and at FR 73A, LH and RC require approval of an AMOC. on a substantial number of small entities RH sides on Model A310 airplanes; in (j) Related Information accordance with the Accomplishment under the criteria of the Regulatory Instructions of Airbus Service Bulletin A310– Refer to Mandatory Continuing Flexibility Act. 53–2138, dated May 28, 2014; or Airbus Airworthiness Information (MCAI) EASA AD Service Bulletin A300–53–6175, dated May 2014–0202R1, dated September 19, 2014, for List of Subjects in 14 CFR Part 39 related information. This MCAI may be 28, 2014; as applicable. Repeat the HFEC Air transportation, Aircraft, Aviation inspection thereafter at intervals not to found in the AD docket on the Internet at safety, Incorporation by reference, exceed 7,500 flight cycles. http://www.regulations.gov by searching for Safety. (1) Before the accumulation of 32,000 total and locating Docket No. FAA–2016–0466. flight cycles. (k) Material Incorporated by Reference Adoption of the Amendment (2) Within 36 months after the effective date of this AD, or before the accumulation (1) The Director of the Federal Register Accordingly, under the authority approved the incorporation by reference delegated to me by the Administrator, of 36,000 total flight cycles, whichever (IBR) of the service information listed in this the FAA amends 14 CFR part 39 as occurs first. paragraph under 5 U.S.C. 552(a) and 1 CFR follows: (h) Corrective Actions part 51. If any crack is found during any inspection (2) You must use this service information PART 39—AIRWORTHINESS required by paragraph (g) of this AD, repair as applicable to do the actions required by DIRECTIVES before further flight using a method approved this AD, unless this AD specifies otherwise. by the Manager, International Branch, ANM– (i) Airbus Service Bulletin A300–53–6175, ■ 1. The authority citation for part 39 116, Transport Airplane Directorate, FAA; or dated May 28, 2014. continues to read as follows: the European Aviation Safety Agency (ii) Airbus Service Bulletin A310–53–2138, dated May 28, 2014. Authority: 49 U.S.C. 106(g), 40113, 44701. (EASA); or Airbus’s EASA Design (3) For service information identified in Organization Approval (DOA). this AD, contact Airbus SAS, Airworthiness § 39.13 [Amended] (i) Other FAA AD Provisions Office—EAW, 1 Rond Point Maurice ■ 2. The FAA amends § 39.13 by adding The following provisions also apply to this Bellonte, 31707 Blagnac Cedex, France; the following new airworthiness AD: telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ directive (AD): (1) Alternative Methods of Compliance (AMOCs): The Manager, International airbus.com; Internet http://www.airbus.com. 2016–16–06 Airbus: Amendment 39–18604; (4) You may view this service information Branch, ANM–116, Transport Airplane Docket No. FAA–2016–0466; Directorate at the FAA, Transport Airplane Directorate, Directorate, FAA, has the authority to Identifier 2014–NM–188–AD. 1601 Lind Avenue SW., Renton, WA. For approve AMOCs for this AD, if requested (a) Effective Date using the procedures found in 14 CFR 39.19. information on the availability of this In accordance with 14 CFR 39.19, send your material at the FAA, call 425–227–1221. This AD is effective September 8, 2016. (5) You may view this service information request to your principal inspector or local (b) Affected ADs Flight Standards District Office, as that is incorporated by reference at the appropriate. If sending information directly National Archives and Records None. Administration (NARA). For information on to the International Branch, send it to ATTN: (c) Applicability Dan Rodina, Aerospace Engineer, the availability of this material at NARA, call International Branch, ANM–116, Transport 202–741–6030, or go to: http:// This AD applies to Airbus Model A300 B4– Airplane Directorate, FAA, 1601 Lind www.archives.gov/federal-register/cfr/ibr- 603, A300 B4–605R, A300 B4–622R, A310– Avenue SW., Renton, WA 98057–3356; locations.html. 304, A310–324, and A310–325 airplanes; certificated in any category; all manufacturer telephone 425–227–2125; fax 425–227–1149. Issued in Renton, Washington, on July 21, ehiers on DSK5VPTVN1PROD with RULES serial numbers (MSNs) in post-modification Information may be emailed to: 9-ANM-116- 2016. (MOD) 06924 configuration, except MSNs AMOC-REQUESTS@faa.gov. Before using Michael Kaszycki, 464, 477, 479, 481, 482, 483, 484, and 488. any approved AMOC, notify your appropriate Acting Manager, Transport Airplane Note 1 to paragraph (c) of this AD: MSNs principal inspector, or lacking a principal Directorate, Aircraft Certification Service. 464, 477, 479, 481, 482, 483, 484 and 488 inspector, the manager of the local flight partially embodied MOD 06924 by means of standards district office/certificate holding [FR Doc. 2016–18254 Filed 8–3–16; 8:45 am] modification proposal D05902. district office. BILLING CODE 4910–13–P VerDate Sep<11>2014 13:37 Aug 03, 2016 Jkt 238001 PO 00000 Frm 00026 Fmt 4700 Sfmt 9990 E:\FR\FM\04AUR1.SGM 04AUR1


Document Created: 2016-08-04 02:53:31
Document Modified: 2016-08-04 02:53:31
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionRules and Regulations
ActionFinal rule.
DatesThis AD is effective September 8, 2016.
ContactDan 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.
FR Citation81 FR 51320 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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