[Federal Register Volume 82, Number 159 (Friday, August 18, 2017)]
[Rules and Regulations]
[Pages 39351-39355]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-16359]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9052; Product Identifier 2016-NM-080-AD; Amendment 
39-18983; AD 2017-16-06]
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 series airplanes; Model A300 B4-600, B4-600R, and F4-
600R series airplanes, and Model A300 C4-605R Variant F airplanes 
(collectively called Model A300-600 series airplanes); and Model A310 
series airplanes. This AD was prompted by reports of failure of an aft 
hinge bolt assembly in the nose landing gear (NLG) aft doors. This AD 
requires replacement of the aft hinge bolt assembly in the left and 
right NLG aft doors, with new aft hinge bolt assemblies. We are issuing 
this AD to address the unsafe condition on these products.

DATES: This AD is effective September 22, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 22, 
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://

[[Page 39352]]

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-2016-
9052.

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-
9052; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Office (telephone 
800-647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 1601 Lind 
Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-
1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus Model A300 
series airplanes; Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and Model A300 C4-605R Variant F airplanes (collectively 
called Model A300-600 series airplanes); and Model A310 series 
airplanes. The NPRM published in the Federal Register on August 30, 
2016 (81 FR 59546) (``the NPRM''). The NPRM was prompted by reports of 
failure of an aft hinge bolt assembly in the NLG aft doors. The NPRM 
proposed to require replacement of the aft hinge bolt assembly in the 
left and right NLG aft doors, with new aft hinge bolt assemblies. We 
are issuing this AD to prevent failure of an aft hinge bolt assembly in 
an NLG aft door while the airplane is in flight, which could lead to an 
in-flight loss of an NLG aft door, and damage to the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2016-0100, dated May 24, 2016 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for all Airbus Model A300 series airplanes; Model A300 
B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R 
Variant F airplanes (collectively called Model A300-600 series 
airplanes); and Model A310 series airplanes. The MCAI states:

    An occurrence has been reported of failure of a nose landing 
gear (NLG) door aft hinge bolt assembly, Part Number (P/N) 
A53612600000. The result of laboratory investigations revealed that 
the aft hinge bolt rupture was initiated by fatigue crack 
development in the under head radius of the bolt, due to the lack of 
radius roll over and in combination with a non-optimised design.
    This condition, if not detected and corrected, could lead to in-
flight loss of an aft NLG door, possibly resulting in damage to the 
aeroplane and injury to persons on the ground.
    Prompted by these findings, Airbus developed a new design aft 
hinge bolt assembly P/N A53612713000, introduced as Airbus 
modification (mod) 13741, to replace the existing bolt P/N 
A53612600000. Since the introduction of that mod, additional stress 
calculations demonstrated that the new bolt assembly, P/N 
A53612713000, cannot sustain fatigue loads up to the design Limit of 
Validity (LOV) of the affected aeroplanes.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A300-53-0397, SB A310-53-2144 and SB A300-53-
6186, to provide instructions for the repetitive replacement of the 
affected post-mod 13741 P/N A53612713000 aft hinge bolts.
    For the reasons described above, this [EASA] AD requires the 
replacement of all P/N A53612600000 aft hinge bolt assemblies, 
installed on the left hand (LH) and right hand (RH) NLG aft doors, 
with post-mod 13741 P/N A53612713000 aft hinge bolt assemblies, and, 
subsequently, the implementation of a life limit for those new bolt 
assemblies.

    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-
9052.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Request To Withdraw the NPRM

    FedEx stated it does not agree that the proposed hinge bolt 
replacement is necessary, asserting that the severity of a failed 
condition does not equate to an unsafe condition on the airplane. FedEx 
explained that in the last 22 years of flight operations, it has not 
had a departure of the NLG door, nor has it seen any cracking of the 
aft hinge bolt.
    From this statement, we infer that FedEx requested we withdraw the 
NPRM. We disagree with this request. Airbus has records of multiple 
instances of hinge bolt failures. Failure of an aft hinge bolt assembly 
in an NLG aft door while the airplane is in flight could lead to an in-
flight loss of an NLG aft door, and damage to the airplane. We have not 
changed this AD in this regard.

Request To Allow Option for Repetitive Inspections

    FedEx requested that a repetitive non-destructive test (NDT) 
technique be allowed as an option to replacing the affected bolts. 
FedEx stated that a routine NDT inspection would be best suited for 
this condition and that the affected bolts should only be replaced as 
an on-condition action. Further, FedEx stated that the proposed 
requirement to replace all affected bolts will be a financial burden on 
operators. FedEx also pointed out that the two bolts required for each 
airplane are $2,300, and these bolts will be required to be replaced 
every 10,000 flight cycles (approximately every 10 years). FedEx 
further requested that the FAA petition the EASA to revise the Airbus 
service information to permit the repetitive inspection as an option to 
the required bolt replacement.
    We disagree with the commenter's request. The intent of this AD is 
to regularly replace the affected hinge bolt with a new one. The bolt 
loading and fatigue spectrum is complex, and the manufacturer is not 
able to substantiate a fatigue life to support a repeat inspection 
program. Therefore, we have made no changes to this AD in this regard. 
However, under the provisions of paragraph (k)(1) of this AD, we will 
consider requests for approval of an alternative method of compliance 
(AMOC) if sufficient data are submitted to substantiate that the change 
would provide an acceptable level of safety.

Request To Remove the Requirement To Replace Aft Hinge Bolts

    United Parcel Service (UPS) requested that we revise the proposed 
AD to remove the requirement to replace aft hinge bolts. UPS contended 
that the more appropriate method for implementation of the repetitive 
10,000-flight-cycle replacement of the hinge bolt assembly would be 
through a maintenance program revision, or incorporation into the Safe 
Life Airworthiness Limitation Items (SL ALI)--Part 1. Therefore, UPS 
recommended that we delete the proposed hinge bolt replacement, and

[[Page 39353]]

instead coordinate with EASA to revise the SL ALI to include the hinge 
bolt assembly.
    We disagree with the commenter's request. Only parts that are 
identified as a safe life part are incorporated into the SL ALI. The 
specified hinge bolt does not meet the Airbus Airworthiness Limitations 
Section (ALS) Part 1 criteria for a safe life part. The hinge bolt does 
not have fatigue testing or demonstrated fatigue life analysis, which 
is required for safe life parts. We have not changed this AD in this 
regard.

Request To Combine Certain Service Information

    UPS requested that, if its request to revise the proposed AD to 
remove the hinge assembly replacement is unacceptable to the FAA, we 
revise paragraph (h)(3) of this proposed AD to require removal and 
installation of a new bolt using only Airbus Service Bulletin A300-53-
6182 and not list Airbus Service Bulletin A300-53-6186. UPS explained 
that the final result of the proposed AD is the replacement of the bolt 
in every case; however, Airbus Service Bulletin A300-53-6186 specifies 
doing an inspection of the bolt part number in addition to the 
replacement and is an added burden to the operator given the location 
of the identifying mark and the difficulty accessing that mark.
    We disagree with the commenter's request because paragraphs (g) and 
(h) of this AD and the corresponding service information are necessary 
to distinguish between two different actions with different compliance 
times:
     Paragraph (g) of this AD and corresponding service 
information for the introduction of the bolt's new design.
     Paragraph (h) of this AD and corresponding service 
bulletin for regular bolt replacement, which includes an inspection for 
verification if the proper bolt part number was installed.
    While it might be difficult for operators to identify the part 
number of the bolt when it is installed on the aircraft, the bolt is 
scheduled to be removed so it should not be difficult to verify that 
the correct part was installed. We have not changed this AD in this 
regard.

Request To Update Illustrated Parts Catalog (IPC) To Show the Post-
Modification Part Number

    UPS requested that the FAA coordinate with EASA and Airbus to 
ensure that the IPC is updated to show only the post-modification part 
number prior to the AD being issued. UPS was concerned that an outdated 
IPC creates opportunities for installation of the original, non-
compliant bolt assembly.
    We infer that UPS was also requesting that we delay publication of 
the final rule pending revision of the IPC. We disagree with this 
request. Airbus has informed the FAA that the IPC is scheduled to be 
revised. However, we do not consider that delaying this action until 
after the release of the manufacturer's revised IPC is warranted, since 
sufficient information currently exists in this AD and the required 
service information to address the identified unsafe condition. We have 
not changed this AD in this regard.

Clarification of Corrective Action

    We have clarified the corrective actions in the introductory text 
of paragraph (h) of this AD by referring to paragraph (k)(2) of this 
AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD as proposed except for minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed the following Airbus service information.
     Airbus Service Bulletin A300-53-0396, dated November 25, 
2015.
     Airbus Service Bulletin A300-53-6182, dated November 17, 
2015.
     Airbus Service Bulletin A310-53-2142, dated November 17, 
2015.
    This service information describes procedures for replacement of 
the aft hinge bolt assemblies in the left and right NLG aft doors, with 
new aft hinge bolt assemblies. These documents are distinct since they 
apply to different airplane models and configurations.
    We also reviewed the following Airbus service information.
     Airbus Service Bulletin A300-53-0397, dated January 18, 
2016.
     Airbus Service Bulletin A300-53-6186, dated January 18, 
2016.
     Airbus Service Bulletin A310-53-2144, dated January 18, 
2016.
    This service information describes procedures for replacement of 
the aft hinge bolt assemblies in the left and right NLG aft doors, with 
new aft hinge bolt assemblies. The replacement includes an inspection 
to verify if the proper bolt part number was installed and repair if 
the proper bolt part number was not installed. These documents are 
distinct since they apply to different airplane models and 
configurations.
    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 157 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
----------------------------------------------------------------------------------------------------------------
Replacement........................  9 work-hours x $85 per hour          $2,000          $2,765        $434,105
                                      = $765.
----------------------------------------------------------------------------------------------------------------

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

[[Page 39354]]

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.


Sec.  39.13  [Amended]

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

2017-16-06 Airbus: Amendment 39-18983; Docket No. FAA-2016-9052; 
Product Identifier 2016-NM-080-AD.

(a) Effective Date

    This AD is effective September 22, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus airplanes identified in paragraphs 
(c)(1) through (c)(6) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and 
B4-203 airplanes.
    (2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
    (3) Model A300 B4-605R and B4-622R airplanes.
    (4) Model A300 F4-605R and F4-622R airplanes.
    (5) Model A300 C4-605R Variant F airplanes.
    (6) Model A310-203, -204, -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 reports of failure of an aft hinge bolt 
assembly in the nose landing gear (NLG) aft doors. We are issuing 
this AD to prevent failure of an aft hinge bolt assembly in an NLG 
aft door while the airplane is in flight, which could lead to an in-
flight loss of an NLG aft door, and damage to the airplane.

(f) Compliance

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

(g) Replacement of Aft Hinge Bolt Assemblies Having Part Number (P/N) 
A53612600000

    Before the accumulation of 10,000 total flight cycles since 
first flight of the airplane, or within 2,000 flight cycles after 
the effective date of this AD, whichever occurs later: Replace each 
aft hinge bolt assembly having P/N A53612600000 on the left and 
right NLG aft doors, with a new hinge bolt assembly having P/N 
A53612713000, in accordance with the Accomplishment Instructions of 
the applicable service information identified in paragraph (g)(1), 
(g)(2), or (g)(3) of this AD.
    (1) Airbus Service Bulletin A300-53-0396, dated November 25, 
2015.
    (2) Airbus Service Bulletin A310-53-2142, dated November 17, 
2015.
    (3) Airbus Service Bulletin A300-53-6182, dated November 17, 
2015.

(h) Replacement of Aft Hinge Bolt Assemblies Having P/N A53612713000

    Within 10,000 flight cycles after modification of an airplane as 
required by paragraph (g) of this AD: Replace each aft hinge bolt 
assembly having P/N A53612713000 on the left and right NLG aft 
doors, with a new aft hinge bolt assembly having P/N A53612713000 on 
the left and right NLG aft doors, in accordance with the 
Accomplishment Instructions of the applicable service information 
specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD, except 
where the service information specified in paragraph (h)(1), (h)(2), 
or (h)(3) of this AD specifies to contact Airbus for instructions, 
before further flight repair using the procedure in paragraph (k)(2) 
of this AD. Repeat the replacement thereafter at intervals not to 
exceed 10,000 flight cycles.
    (1) Airbus Service Bulletin A300-53-0397, dated January 18, 
2016.
    (2) Airbus Service Bulletin A310-53-2144, dated January 18, 
2016.
    (3) Airbus Service Bulletin A300-53-6186, dated January 18, 
2016.

(i) Parts Installation Prohibition (P/N A53612600000)

    After modification of an airplane NLG aft door as required by 
paragraph (g) of this AD, do not install an aft hinge bolt assembly 
having P/N A53612600000 on any NLG aft door of that airplane.

(j) Parts Installation Limitation (P/N A53612713000)

    After removal of an aft hinge bolt assembly having P/N 
A53612713000 from an airplane NLG aft door, as required by paragraph 
(h) of this AD, do not install an aft hinge bolt assembly having 
that part number on that airplane unless it is a new aft hinge bolt 
assembly.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Section, send it to the attention of 
the person identified in paragraph (l)(2) of this AD. Information 
may be emailed to: [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 the European Aviation 
Safety Agency (EASA); or Airbus's EASA Design Organization Approval 
(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

[[Page 39355]]

an airworthy condition. Any substitutions or changes to procedures 
or tests identified as RC require approval of an AMOC.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0100, dated May 24, 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-2016-9052.
    (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.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A300-53-0396, dated November 25, 
2015.
    (ii) Airbus Service Bulletin A300-53-0397, dated January 18, 
2016.
    (iii) Airbus Service Bulletin A300-53-6182, dated November 17, 
2015.
    (iv) Airbus Service Bulletin A300-53-6186, dated January 18, 
2016.
    (v) Airbus Service Bulletin A310-53-2142, dated November 17, 
2015.
    (vi) Airbus Service Bulletin A310-53-2144, dated January 18, 
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 July 26, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-16359 Filed 8-17-17; 8:45 am]
 BILLING CODE 4910-13-P