
[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 account.airworth-eas@airbus.com; 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.

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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: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 

approved AMOC, notify your appropriate principal inspector, or 

lacking a principal inspector, the manager of the local flight 

standards district office/certificate holding district office.

    (2) Contacting the Manufacturer: For any requirement in this AD 

to obtain corrective actions from a manufacturer, the action must be 

accomplished using a method approved by the Manager, International 

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 account.airworth-eas@airbus.com; 

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




