82_FR_43345 82 FR 43168 - Airworthiness Directives; Airbus Airplanes

82 FR 43168 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 82, Issue 177 (September 14, 2017)

Page Range43168-43170
FR Document2017-19043

We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-600R and Model A300 F4-600R series airplanes; Model A300 B4-603, B4-622, and C4-605R Variant F airplanes; and Model A310-203, -221, -222, -304, -322, -324, and -325 airplanes. This AD was prompted by an evaluation by the design approval holder indicating that a section of the fuselage structure above the forward cargo door is subject to widespread fatigue damage (WFD). This AD requires an inspection for cracks of the fastener and tooling holes at certain locations and a check of the diameter of the holes, and repair or modification of the affected fuselage structure if necessary. We are issuing this AD to address the unsafe condition on these products.

Federal Register, Volume 82 Issue 177 (Thursday, September 14, 2017) 
[Federal Register Volume 82, Number 177 (Thursday, September 14, 2017)]
[Rules and Regulations]
[Pages 43168-43170]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2017-19043]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0533; Product Identifier 2016-NM-156-AD; Amendment 
39-19024; AD 2017-18-15]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A300 B4-600R and Model A300 F4-600R series airplanes; 
Model A300 B4-603, B4-622, and C4-605R Variant F airplanes; and Model 
A310-203, -221, -222, -304, -322, -324, and -325 airplanes. This AD was 
prompted by an evaluation by the design approval holder indicating that 
a section of the fuselage structure above the forward cargo door is 
subject to widespread fatigue damage (WFD). This AD requires an 
inspection for cracks of the fastener and tooling holes at certain 
locations and a check of the diameter of the holes, and repair or 
modification of the affected fuselage structure if necessary. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective October 19, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 19, 
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 [email protected]; 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-
0533.

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-
0533; 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 B4-
600R and Model A300 F4-600R series airplanes; Model A300 B4-603, B4-
622, and C4-605R Variant F airplanes; and Model A310-203, -221, -222, -
304, -322, -324, and -325 airplanes. The NPRM published in the Federal 
Register on June 12, 2017 (82 FR 26874) (``the NPRM''). The NPRM was 
prompted by an evaluation by the design approval holder indicating that 
a section of the fuselage structure above the forward cargo door is 
subject to WFD. The NPRM proposed to require an inspection for cracks 
of the fastener and tooling holes at certain locations and a check of 
the diameter of the holes, and repair or modification of the affected 
fuselage structure if necessary. We are issuing this AD to prevent 
reduced structural integrity of these airplanes due to the failure of 
certain structural components.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0178, dated September 12, 2016 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A300 
B4-600R and Model A300 F4-600R series airplanes; Model A300 B4-603, B4-
622, and C4-605R Variant F airplanes; and Model A310-203, -221, -222, -
304, -322, -324, and -325 airplanes. The MCAI states:

    In the frame of the Widespread Fatigue Damage (WFD) analysis, 
some structural

[[Page 43169]]

areas were identified as requiring embodiment of a structural 
modification.
    This condition, if not corrected, could reduce the fuselage 
structural integrity.
    To address this unsafe condition, Airbus issued Service Bulletin 
(SB) A310-53-2145 and SB A300-53-6187 to provide instructions for 
structural reinforcement of the fuselage frames (FR) between FR20 
Right Hand side (RH) and FR25 RH and the frame couplings between 
stringer (STGR) 20 RH and STGR23 RH, hereafter collectively referred 
to as `the affected fuselage structure' in this [EASA] AD.
    For the reason described above, this [EASA] AD requires 
accomplishment of a one-time special detailed inspection (SDI) of 
the fastener and tooling holes, and modification of the affected 
fuselage structure.

    The required actions include a rototest inspection for cracks of 
the fastener and tooling holes at certain locations and a check of the 
diameter of the holes, and repair or modification of the affected 
fuselage structure if necessary. 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-2017-0533.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. The commenter supported 
the NPRM.

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 the following service information.
     Airbus Service Bulletin A300-53-6187, Revision 00, dated 
May 31, 2016. This service information describes procedures for a 
rototest inspection for cracks of the fastener and tooling holes at 
certain locations, a check of the diameter of the holes, repair, and 
modification of the affected fuselage structure by reinforcing the 
frames between right hand (RH) frame (FR) 20 RH and FR25 RH, or FR21 RH 
and FR25 RH, depending on the configuration; and reinforcing the frame 
couplings between stringer (STGR) 20 RH and STGR23 RH.
     Airbus Service Bulletin A310-53-2145, Revision 00, dated 
May 31, 2016. This service information describes procedures for a 
rototest inspection for cracks of the fastener and tooling holes at 
certain locations, a check of the diameter of the holes, repair, and 
modification of the affected fuselage structure by reinforcing the 
frames between right hand FR20 RH and FR25 RH; and reinforcing the 
frame couplings between STGR20 RH and STGR23 RH.
    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 132 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection, check, repair, and          45 work-hours x $85 per           $2,360          $6,185        $816,420
 modification.                           hour = $3,825.
----------------------------------------------------------------------------------------------------------------

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, 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.

[[Page 43170]]

Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2017-18-15 Airbus: Amendment 39-18024; Docket No. FAA-2017-0533; 
Product Identifier 2016-NM-156-AD.

(a) Effective Date

    This AD is effective October 19, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus airplanes identified in paragraphs 
(c)(1) through (c)(5) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Model A300 B4-603 and A300 B4-622 airplanes.
    (2) Model A300 B4-605R and A300 B4-622R airplanes.
    (3) Model A300 F4-605R and A300 F4-622R airplanes.
    (4) Model A300 C4-605R Variant F airplanes.
    (5) Model A310-203, -221, -222, -304, -322, -324, and -325 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder indicating that a section of the fuselage structure above the 
forward cargo door is subject to widespread fatigue damage. We are 
issuing this AD to prevent reduced structural integrity of these 
airplanes due to the failure of certain structural components.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Check and Rototest Inspection of Affected Fastener and Tooling 
Holes

    Before exceeding 42,500 flight cycles since the first flight of 
the airplane, do a check of the diameter of the fastener holes and 
tooling holes and a rototest inspection for cracks of all holes of 
removed fasteners and the tooling holes at the locations specified 
in, and in accordance with, the Accomplishment Instructions of 
Airbus Service Bulletin A300-53-6187, Revision 00, dated May 31, 
2016; or Airbus Service Bulletin A310-53-2145, Revision 00, dated 
May 31, 2016; as applicable.

(h) Repair

    If any condition specified in paragraph (h)(1) or (h)(2) of this 
AD is found, prior to further flight, repair in accordance with 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). 
Concurrently with the repair, unless the approved repair 
instructions specify otherwise, modify the affected structure, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6187, Revision 00, dated May 31, 2016; or Airbus 
Service Bulletin A310-53-2145, Revision 00, dated May 31, 2016; as 
applicable.
    (1) Any crack is found during the rototest inspection required 
by paragraph (g) of this AD.
    (2) Any hole diameter greater than or equal to the maximum 
starting hole diameter specified in the Accomplishment Instructions 
of Airbus Service Bulletin A300-53-6187, Revision 00, dated May 31, 
2016; or Airbus Service Bulletin A310-53-2145, Revision 00, dated 
May 31, 2016; as applicable, is found during the check required by 
paragraph (g) of this AD.

(i) Modification

    If, during the actions required by paragraph (g) of this AD, no 
crack is found and the hole diameter is less than the maximum 
starting hole diameter specified in the Accomplishment Instructions 
of Airbus Service Bulletin A300-53-6187, Revision 00, dated May 31, 
2016; or Airbus Service Bulletin A310-53-2145, Revision 00, dated 
May 31, 2016; as applicable: Before further flight, modify the 
affected fuselage structure, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-6187, Revision 00, 
dated May 31, 2016; or Airbus Service Bulletin A310-53-2145, 
Revision 00, dated May 31, 2016; as applicable.

(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: [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 
Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA 
DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0178, dated September 12, 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-2017-0533.
    (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 Service Bulletin A300-53-6187, Revision 00, dated May 
31, 2016.
    (ii) Airbus Service Bulletin A310-53-2145, Revision 00, dated 
May 31, 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 [email protected]; 
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/ibr-locations.html.


    Issued in Renton, Washington, on August 29, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-19043 Filed 9-13-17; 8:45 am]
 BILLING CODE 4910-13-P

43168 Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations inspector, the manager of the local flight DEPARTMENT OF TRANSPORTATION 0533; or in person at the Docket standards district office/certificate holding Management Facility between 9 a.m. district office. Federal Aviation Administration and 5 p.m., Monday through Friday, (2) Contacting the Manufacturer: For any except Federal holidays. The AD docket requirement in this AD to obtain corrective 14 CFR Part 39 contains this AD, the regulatory actions from a manufacturer, the action must evaluation, any comments received, and be accomplished using a method approved [Docket No. FAA–2017–0533; Product Identifier 2016–NM–156–AD; Amendment other information. The street address for by the Manager, International Section, 39–19024; AD 2017–18–15] the Docket Office (telephone 800–647– Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or 5527) is Docket Management Facility, RIN 2120–AA64 Dassault Aviation’s EASA Design U.S. Department of Transportation, Organization Approval (DOA). If approved by Airworthiness Directives; Airbus Docket Operations, M–30, West the DOA, the approval must include the Airplanes Building Ground Floor, Room W12–140, DOA-authorized signature. 1200 New Jersey Avenue SE., AGENCY: Federal Aviation Washington, DC 20590. (k) Related Information Administration (FAA), Department of FOR FURTHER INFORMATION CONTACT: Dan (1) Refer to Mandatory Continuing Transportation (DOT). Rodina, Aerospace Engineer, Airworthiness Information (MCAI) EASA ACTION: Final rule. International Section, Transport Airworthiness Directive 2016–0127, dated June 23, 2016, for related information. This Standards Branch, FAA, 1601 Lind SUMMARY: We are adopting a new MCAI may be found in the AD docket on the Avenue SW., Renton, WA 98057–3356; airworthiness directive (AD) for all Internet at http://www.regulations.gov by telephone 425–227–2125; fax 425–227– Airbus Model A300 B4–600R and Model searching for and locating Docket No. FAA– 1149. A300 F4–600R series airplanes; Model 2017–0525. A300 B4–603, B4–622, and C4–605R SUPPLEMENTARY INFORMATION: (2) For more information about this AD, Variant F airplanes; and Model A310– contact Tom Rodriguez, Aerospace Engineer, Discussion 203, –221, –222, –304, –322, –324, and International Section, Transport Standards We issued a notice of proposed –325 airplanes. This AD was prompted Branch, FAA, 1601 Lind Avenue SW., by an evaluation by the design approval rulemaking (NPRM) to amend 14 CFR Renton, WA 98057–3356; telephone 425– holder indicating that a section of the part 39 by adding an AD that would 227–1137; fax 425–227–1149. fuselage structure above the forward apply to all Airbus Model A300 B4– (l) Material Incorporated by Reference cargo door is subject to widespread 600R and Model A300 F4–600R series (1) The Director of the Federal Register fatigue damage (WFD). This AD requires airplanes; Model A300 B4–603, B4–622, approved the incorporation by reference an inspection for cracks of the fastener and C4–605R Variant F airplanes; and (IBR) of the service information listed in this and tooling holes at certain locations Model A310–203, –221, –222, –304, paragraph under 5 U.S.C. 552(a) and 1 CFR and a check of the diameter of the holes, –322, –324, and –325 airplanes. The part 51. and repair or modification of the NPRM published in the Federal (2) You must use this service information affected fuselage structure if necessary. Register on June 12, 2017 (82 FR 26874) as applicable to do the actions required by We are issuing this AD to address the (‘‘the NPRM’’). The NPRM was this AD, unless this AD specifies otherwise. unsafe condition on these products. prompted by an evaluation by the (i) Chapter 5–40, Airworthiness design approval holder indicating that a DATES: This AD is effective October 19, Limitations, Revision 22, dated December section of the fuselage structure above 2015, of the Dassault Aviation Falcon 900 2017. The Director of the Federal Register the forward cargo door is subject to Maintenance Manual. WFD. The NPRM proposed to require an (ii) Reserved. approved the incorporation by reference of certain publications listed in this AD inspection for cracks of the fastener and (3) For service information identified in as of October 19, 2017. tooling holes at certain locations and a this AD, contact Dassault Falcon Jet check of the diameter of the holes, and Corporation, Teterboro Airport, P.O. Box ADDRESSES: For service information 2000, South Hackensack, NJ 07606; repair or modification of the affected identified in this final rule, contact telephone 201–440–6700; Internet http:// fuselage structure if necessary. We are Airbus SAS, Airworthiness Office— www.dassaultfalcon.com. issuing this AD to prevent reduced EAW, 1 Rond Point Maurice Bellonte, (4) You may view this service information structural integrity of these airplanes 31707 Blagnac Cedex, France; telephone at the FAA, Transport Standards Branch, due to the failure of certain structural +33 5 61 93 36 96; fax +33 5 61 93 44 1601 Lind Avenue SW., Renton, WA. For components. 51; email account.airworth-eas@ information on the availability of this The European Aviation Safety Agency airbus.com; Internet http:// material at the FAA, call 425–227–1221. (EASA), which is the Technical Agent www.airbus.com. You may view this (5) You may view this service information for the Member States of the European that is incorporated by reference at the referenced service information at the FAA, Transport Standards Branch, 1601 Union, has issued EASA Airworthiness National Archives and Records Directive 2016–0178, dated September Administration (NARA). For information on Lind Avenue SW., Renton, WA. For information on the availability of this 12, 2016 (referred to after this as the the availability of this material at NARA, call material at the FAA, call 425–227–1221. Mandatory Continuing Airworthiness 202–741–6030, or go to: http:// It is also available on the Internet at Information, or ‘‘the MCAI’’), to correct www.archives.gov/federal-register/cfr/ibr- locations.html. http://www.regulations.gov by searching an unsafe condition for all Airbus for and locating Docket No. FAA–2017– Model A300 B4–600R and Model A300 Issued in Renton, Washington, on August F4–600R series airplanes; Model A300 rmajette on DSKBCKNHB2PROD with RULES 31, 2017. 0533. B4–603, B4–622, and C4–605R Variant F Dionne Palermo, Examining the AD Docket airplanes; and Model A310–203, –221, Acting Director, System Oversight Division, You may examine the AD docket on –222, –304, –322, –324, and –325 Aircraft Certification Service. the Internet at http:// airplanes. The MCAI states: [FR Doc. 2017–19302 Filed 9–13–17; 8:45 am] www.regulations.gov by searching for In the frame of the Widespread Fatigue BILLING CODE 4910–13–P and locating Docket No. FAA–2017– Damage (WFD) analysis, some structural VerDate Sep<11>2014 15:11 Sep 13, 2017 Jkt 241001 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 E:\FR\FM\14SER1.SGM 14SER1

Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations 43169 areas were identified as requiring Comments modification of the affected fuselage embodiment of a structural modification. structure by reinforcing the frames We gave the public the opportunity to This condition, if not corrected, could between right hand (RH) frame (FR) 20 participate in developing this AD. We reduce the fuselage structural integrity. RH and FR25 RH, or FR21 RH and FR25 considered the comment received. The To address this unsafe condition, Airbus RH, depending on the configuration; commenter supported the NPRM. issued Service Bulletin (SB) A310–53–2145 and reinforcing the frame couplings and SB A300–53–6187 to provide Conclusion between stringer (STGR) 20 RH and instructions for structural reinforcement of We reviewed the relevant data, STGR23 RH. the fuselage frames (FR) between FR20 Right considered the comment received, and • Airbus Service Bulletin A310–53– Hand side (RH) and FR25 RH and the frame determined that air safety and the 2145, Revision 00, dated May 31, 2016. couplings between stringer (STGR) 20 RH public interest require adopting this AD This service information describes and STGR23 RH, hereafter collectively as proposed except for minor editorial procedures for a rototest inspection for referred to as ‘the affected fuselage structure’ changes. We have determined that these cracks of the fastener and tooling holes in this [EASA] AD. minor changes: at certain locations, a check of the For the reason described above, this • Are consistent with the intent that [EASA] AD requires accomplishment of a diameter of the holes, repair, and was proposed in the NPRM for modification of the affected fuselage one-time special detailed inspection (SDI) of correcting the unsafe condition; and structure by reinforcing the frames the fastener and tooling holes, and • Do not add any additional burden between right hand FR20 RH and FR25 modification of the affected fuselage upon the public than was already structure. RH; and reinforcing the frame couplings proposed in the NPRM. between STGR20 RH and STGR23 RH. The required actions include a Related Service Information Under 1 This service information is reasonably rototest inspection for cracks of the CFR Part 51 available because the interested parties fastener and tooling holes at certain Airbus has issued the following have access to it through their normal locations and a check of the diameter of service information. course of business or by the means the holes, and repair or modification of • Airbus Service Bulletin A300–53– identified in the ADDRESSES section. the affected fuselage structure if 6187, Revision 00, dated May 31, 2016. Costs of Compliance necessary. You may examine the MCAI This service information describes in the AD docket on the Internet at procedures for a rototest inspection for We estimate that this AD affects 132 http://www.regulations.gov by searching cracks of the fastener and tooling holes airplanes of U.S. registry. for and locating Docket No. FAA–2017– at certain locations, a check of the We estimate the following costs to 0533. diameter of the holes, repair, and comply with this AD: ESTIMATED COSTS Cost per Cost on U.S. Action Labor cost Parts cost product operators Inspection, check, repair, and modification .... 45 work-hours × $85 per hour = $3,825 ........ $2,360 $6,185 $816,420 Authority for This Rulemaking In accordance with that order, issuance 3. Will not affect intrastate aviation in Title 49 of the United States Code of ADs is normally a function of the Alaska; and specifies the FAA’s authority to issue Compliance and Airworthiness 4. Will not have a significant rules on aviation safety. Subtitle I, Division, but during this transition economic impact, positive or negative, section 106, describes the authority of period, the Executive Director has on a substantial number of small entities the FAA Administrator. ‘‘Subtitle VII: delegated the authority to issue ADs under the criteria of the Regulatory Aviation Programs,’’ describes in more applicable to transport category Flexibility Act. detail the scope of the Agency’s airplanes to the Director of the System authority. Oversight Division. List of Subjects in 14 CFR Part 39 We are issuing this rulemaking under Regulatory Findings the authority described in ‘‘Subtitle VII, Air transportation, Aircraft, Aviation Part A, Subpart III, Section 44701: We determined that this AD will not safety, Incorporation by reference, General requirements.’’ Under that have federalism implications under Safety. section, Congress charges the FAA with Executive Order 13132. This AD will Adoption of the Amendment promoting safe flight of civil aircraft in not have a substantial direct effect on air commerce by prescribing regulations the States, on the relationship between Accordingly, under the authority for practices, methods, and procedures the national government and the States, delegated to me by the Administrator, the Administrator finds necessary for or on the distribution of power and the FAA amends 14 CFR part 39 as safety in air commerce. This regulation responsibilities among the various follows: is within the scope of that authority levels of government. because it addresses an unsafe condition For the reasons discussed above, I PART 39—AIRWORTHINESS rmajette on DSKBCKNHB2PROD with RULES that is likely to exist or develop on certify that this AD: DIRECTIVES products identified in this rulemaking action. 1. Is not a ‘‘significant regulatory ■ 1. The authority citation for part 39 This AD is issued in accordance with action’’ under Executive Order 12866; continues to read as follows: authority delegated by the Executive 2. Is not a ‘‘significant rule’’ under the Director, Aircraft Certification Service, DOT Regulatory Policies and Procedures Authority: 49 U.S.C. 106(g), 40113, 44701. as authorized by FAA Order 8000.51C. (44 FR 11034, February 26, 1979); VerDate Sep<11>2014 15:11 Sep 13, 2017 Jkt 241001 PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 E:\FR\FM\14SER1.SGM 14SER1

43170 Federal Register / Vol. 82, No. 177 / Thursday, September 14, 2017 / Rules and Regulations § 39.13 [Amended] accordance with the Accomplishment methods in accordance with the operator’s Instructions of Airbus Service Bulletin A300– maintenance or inspection program without ■ 2. The FAA amends § 39.13 by adding 53–6187, Revision 00, dated May 31, 2016; or obtaining approval of an AMOC, provided the following new airworthiness Airbus Service Bulletin A310–53–2145, directive (AD): the procedures and tests identified as RC can Revision 00, dated May 31, 2016; as be done and the airplane can be put back in 2017–18–15 Airbus: Amendment 39–18024; applicable. an airworthy condition. Any substitutions or Docket No. FAA–2017–0533; Product (1) Any crack is found during the rototest changes to procedures or tests identified as Identifier 2016–NM–156–AD. inspection required by paragraph (g) of this AD. RC require approval of an AMOC. (a) Effective Date (2) Any hole diameter greater than or equal (k) Related Information This AD is effective October 19, 2017. to the maximum starting hole diameter specified in the Accomplishment (1) Refer to Mandatory Continuing (b) Affected ADs Airworthiness Information (MCAI) EASA AD Instructions of Airbus Service Bulletin A300– None. 53–6187, Revision 00, dated May 31, 2016; or 2016–0178, dated September 12, 2016, for (c) Applicability Airbus Service Bulletin A310–53–2145, related information. This MCAI may be Revision 00, dated May 31, 2016; as found in the AD docket on the Internet at This AD applies to Airbus airplanes applicable, is found during the check http://www.regulations.gov by searching for identified in paragraphs (c)(1) through (c)(5) required by paragraph (g) of this AD. and locating Docket No. FAA–2017–0533. of this AD, certificated in any category, all manufacturer serial numbers. (i) Modification (2) For more information about this AD, (1) Model A300 B4–603 and A300 B4–622 contact Dan Rodina, Aerospace Engineer, If, during the actions required by paragraph airplanes. (g) of this AD, no crack is found and the hole International Section, Transport Standards (2) Model A300 B4–605R and A300 B4– diameter is less than the maximum starting Branch, FAA, 1601 Lind Avenue SW., 622R airplanes. hole diameter specified in the Renton, WA 98057–3356; telephone 425– (3) Model A300 F4–605R and A300 F4– Accomplishment Instructions of Airbus 227–2125; fax 425–227–1149. 622R airplanes. Service Bulletin A300–53–6187, Revision 00, (4) Model A300 C4–605R Variant F (l) Material Incorporated by Reference dated May 31, 2016; or Airbus Service airplanes. Bulletin A310–53–2145, Revision 00, dated (1) The Director of the Federal Register (5) Model A310–203, –221, –222, –304, May 31, 2016; as applicable: Before further approved the incorporation by reference –322, –324, and –325 airplanes. flight, modify the affected fuselage structure, (IBR) of the service information listed in this (d) Subject in accordance with the Accomplishment paragraph under 5 U.S.C. 552(a) and 1 CFR Instructions of Airbus Service Bulletin A300– part 51. Air Transport Association (ATA) of 53–6187, Revision 00, dated May 31, 2016; or (2) You must use this service information America Code 53, Fuselage. Airbus Service Bulletin A310–53–2145, as applicable to do the actions required by (e) Reason Revision 00, dated May 31, 2016; as applicable. this AD, unless this AD specifies otherwise. This AD was prompted by an evaluation by (i) Airbus Service Bulletin A300–53–6187, the design approval holder indicating that a (j) Other FAA AD Provisions Revision 00, dated May 31, 2016. section of the fuselage structure above the The following provisions also apply to this (ii) Airbus Service Bulletin A310–53–2145, forward cargo door is subject to widespread AD: Revision 00, dated May 31, 2016. fatigue damage. We are issuing this AD to (1) Alternative Methods of Compliance (3) For service information identified in prevent reduced structural integrity of these airplanes due to the failure of certain (AMOCs): The Manager, International this AD, contact Airbus SAS, Airworthiness structural components. Section, Transport Standards Branch, FAA, Office—EAW, 1 Rond Point Maurice has the authority to approve AMOCs for this Bellonte, 31707 Blagnac Cedex, France; (f) Compliance AD, if requested using the procedures found telephone +33 5 61 93 36 96; fax +33 5 61 Comply with this AD within the in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal 93 44 51; email account.airworth-eas@ compliance times specified, unless already airbus.com; Internet http://www.airbus.com. done. inspector or local Flight Standards District Office, as appropriate. If sending information (4) You may view this service information (g) Check and Rototest Inspection of Affected directly to the International Section, send it at the FAA, Transport Standards Branch, Fastener and Tooling Holes to the attention of the person identified in 1601 Lind Avenue SW., Renton, WA. For Before exceeding 42,500 flight cycles since paragraph (k)(2) of this AD. Information may information on the availability of this the first flight of the airplane, do a check of be emailed to: 9-ANM-116-AMOC- material at the FAA, call 425–227–1221. the diameter of the fastener holes and tooling REQUESTS@faa.gov. Before using any (5) You may view this service information holes and a rototest inspection for cracks of approved AMOC, notify your appropriate that is incorporated by reference at the all holes of removed fasteners and the tooling principal inspector, or lacking a principal National Archives and Records holes at the locations specified in, and in inspector, the manager of the local flight Administration (NARA). For information on accordance with, the Accomplishment standards district office/certificate holding the availability of this material at NARA, call Instructions of Airbus Service Bulletin A300– district office. (2) Contacting the Manufacturer: For any 202–741–6030, or go to: http:// 53–6187, Revision 00, dated May 31, 2016; or Airbus Service Bulletin A310–53–2145, requirement in this AD to obtain corrective www.archives.gov/federal-register/cfr/ibr- Revision 00, dated May 31, 2016; as actions from a manufacturer, the action must locations.html. applicable. be accomplished using a method approved by the Manager, International Section, Issued in Renton, Washington, on August (h) Repair Transport Standards Branch, FAA; or EASA; 29, 2017. If any condition specified in paragraph or Airbus’s EASA DOA. If approved by the Jeffrey E. Duven, (h)(1) or (h)(2) of this AD is found, prior to DOA, the approval must include the DOA- Director, System Oversight Division, Aircraft further flight, repair in accordance with a authorized signature. Certification Service. method approved by the Manager, (3) Required for Compliance (RC): If any rmajette on DSKBCKNHB2PROD with RULES International Section, Transport Standards service information contains procedures or [FR Doc. 2017–19043 Filed 9–13–17; 8:45 am] Branch, FAA; or the European Aviation tests that are identified as RC, those BILLING CODE 4910–13–P Safety Agency (EASA); or Airbus’s EASA procedures and tests must be done to comply Design Organization Approval (DOA). with this AD; any procedures or tests that are Concurrently with the repair, unless the not identified as RC are recommended. Those approved repair instructions specify procedures and tests that are not identified otherwise, modify the affected structure, in as RC may be deviated from using accepted VerDate Sep<11>2014 15:11 Sep 13, 2017 Jkt 241001 PO 00000 Frm 00016 Fmt 4700 Sfmt 9990 E:\FR\FM\14SER1.SGM 14SER1


Document Created: 2017-09-13 23:49:30
Document Modified: 2017-09-13 23:49:30
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 October 19, 2017.
ContactDan 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.
FR Citation82 FR 43168 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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