82 FR 43168 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

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

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, 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