Airworthiness Directives; Airbus Airplanes

[Federal Register Volume 81, Number 246 (Thursday, December 22, 2016)]
[Rules and Regulations]
[Pages 93801-93804]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-30031]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6894; Directorate Identifier 2015-NM-120-AD; 
Amendment 39-18729; AD 2016-25-03]
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 certain 
Airbus Model A300 F4-600R series airplanes. This AD was prompted by a 
report of two adjacent frame forks that were found cracked on the aft 
lower deck cargo door (LDCD) of two Model A300-600F4 airplanes during 
scheduled maintenance. This AD requires repetitive high frequency eddy 
current (HFEC) inspections of the aft LDCD frame forks; a one-time 
check of the LDCD clearances; and a one-time detailed visual inspection 
of hooks, eccentric bushes, and x-stops; and corrective actions if 
necessary. We are issuing this AD to prevent the unsafe condition on 
these products.

DATES: This AD is effective January 26, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 26, 
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 Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6894.

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-
6894; or in person at the Docket Management Facility between 9 a.m.

[[Page 93802]]

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 Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Airbus Model A300 
F4-600R series airplanes. The NPRM published in the Federal Register on 
May 31, 2016 (81 FR 34285) (``the NPRM''). The NPRM was prompted by a 
report of two adjacent frame forks that were found cracked on the aft 
LDCD of two Model A300-600F4 airplanes during scheduled maintenance. 
The NPRM proposed to require repetitive HFEC inspections of the aft 
LDCD frame forks; a one-time check of the LDCD clearances; and a one-
time detailed visual inspection of hooks, eccentric bushes, and x-
stops; and corrective actions if necessary. We are issuing this AD to 
detect and correct cracked or ruptured aft LDCD frames, which could 
allow loads to be transferred to the remaining structural elements.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0152, dated July 24, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A300 
F4-605R and A300 F4-622R airplanes. The MCAI states:

    During scheduled maintenance at frames (FR) 61 and FR61A on the 
aft lower deck cargo door (LDCD) of two A300-600F4 aeroplanes, two 
adjacent frame forks were found cracked.
    Subsequent analysis determined that, in case of cracked or 
ruptured aft cargo door frame(s), loads will be transferred to the 
remaining structural elements. However, these secondary load paths 
will be able to sustain the loads for a limited number of flight 
cycles only.
    This condition, if not detected and corrected, could lead to the 
rupture of one or more vertical aft cargo door frame(s), resulting 
in reduced structural integrity of the aft cargo door.
    To address this unsafe condition, Airbus issued Alert Operators 
Transmission (AOT) A52W011-15 to provide inspection instructions.
    For the reason described above, this [EASA] AD requires 
repetitive inspections [for cracking] of the aft LDCD frame forks 
and, depending on findings, the accomplishment of corrective 
action(s).
    This [EASA] AD is considered interim action and further [EASA] 
AD action may follow.

    Required actions include a one-time check of the LDCD clearances 
and a one-time detailed visual inspection of hooks, eccentric bushes, 
and x-stops; and corrective actions 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-2016-6894.

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 Remove Requirements

    United Parcel Service (UPS) requested that we remove the 
requirements of paragraphs (g)(1) and (g)(2) of the proposed AD because 
the identified work does not contribute to the detection of crack 
formation.
    We do not agree with the request. At this time, Airbus is uncertain 
of the cause of the cracking; it is possible that the affected aircraft 
were incorrectly rigged. Incorrect rigging could lead to an improper 
gap, which could lead to uneven loading on the door frame, thus 
contributing to the cracking. The actions required by paragraphs (g)(1) 
and (g)(2) of this AD are performed only one time and are not repeated. 
No changes have been made to this AD regarding this issue.

Request To Revise Reporting Requirement

    UPS requested that we revise the reporting requirement specified in 
paragraph (i) of the proposed AD. UPS suggested an alternative method 
for submitting inspection results and indicated the alternative would 
add flexibility in the reporting method and maintain the intent of the 
requirement.
    We agree, and have revised paragraph (i) of this AD accordingly.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD with the change described previously and minor editorial 
changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> 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 Alert Operators Transmission (AOT) A52W011-15, 
Revision 00, including Appendices 1, 2, 3, and 4, dated July 23, 2015. 
The service information describes procedures for repetitive HFEC 
inspections for cracking of the aft LDCD frame forks; a one-time check 
of the LDCD clearances; and a one-time detailed visual inspection of 
hooks, eccentric bushes, and x-stops; and corrective actions if 
necessary. 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 58 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
            Action                   Labor cost         Parts cost      Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspections..................  4 work-hours x $85                 $0  $340 per inspection   $19,720 per
                                per hour = $340.                       cycle.                inspection cycle.
Reporting....................  1 work-hour x $85 per               0  $85 per inspection    $4,930 per
                                hour = $85.                            cycle.                inspection cycle.
----------------------------------------------------------------------------------------------------------------


[[Page 93803]]

    We estimate the following costs to do any necessary repairs that 
will be required based on the results of the required inspection. We 
have no way of determining the number of aircraft that might need these 
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
              Action                        Labor cost                  Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Repair............................  Up to 15 work-hours x $85   Up to $10,000.............  Up to $11,275.
                                     per hour = $1,275.
----------------------------------------------------------------------------------------------------------------

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13   [Amended]

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

2016-25-03 Airbus: Amendment 39-18729; Docket No. FAA-2016-6894; 
Directorate Identifier 2015-NM-120-AD.

(a) Effective Date

    This AD is effective January 26, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A300 F4-605R and A300 F4-622R 
airplanes, certificated in any category, on which Airbus 
Modification 12046 has been embodied in production. Modification 
12046 has been embodied in production on manufacturer serial numbers 
(MSNs) 0805 and above, except MSNs 0836, 0837, and 0838.

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

    This AD was prompted by a report of two adjacent frame forks 
that were found cracked on the aft lower deck cargo door (LDCD) of 
two Model A300-600F4 airplanes during scheduled maintenance. We are 
issuing this AD to detect and correct cracked or ruptured aft LDCD 
frames, which could allow loads to be transferred to the remaining 
structural elements. This condition could lead to the rupture of one 
or more vertical aft LDCD frames, which could result in reduced 
structural integrity of the aft LDCD.

(f) Compliance

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

(g) Inspection Requirements

    At the applicable time specified in paragraph (h) of this AD, do 
the actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of 
this AD, in accordance with Airbus Alert Operators Transmission 
(AOT) A52W011-15, Revision 00, dated July 23, 2015.
    (1) Do a one-time check of the aft LDCD clearances ``U'' and 
``V'' between the latching hooks and the eccentric bush at FR60 
through FR64A. If any value outside tolerance is found, adjust the 
latching hook before further flight.
    (2) Do a one-time detailed inspection to detect signs of wear of 
the hooks, eccentric bushes, and x-stops. If any wear is found, do 
all applicable corrective actions before further flight.
    (3) Do a high frequency eddy current (HFEC) inspection to detect 
cracking at all frame fork stations of the aft LDCD. If any crack is 
found, replace the cracked frame fork before further flight. Repeat 
the HFEC inspection thereafter at intervals not to exceed 600 flight 
cycles.

(h) Compliance Times

    At the later of the times specified in paragraphs (h)(1) and 
(h)(2) of this AD, do the actions required by paragraph (g) of this 
AD.
    (1) Before the accumulation of 4,500 total flight cycles.
    (2) At the applicable time specified by paragraph (h)(2)(i) or 
(h)(2)(ii) of this AD.
    (i) For airplanes that have accumulated 8,000 or more total 
flight cycles as of the effective date this AD: Within 100 flight 
cycles after the effective date of this AD.
    (ii) For airplanes that have accumulated fewer than 8,000 total 
flight cycles as of the effective date of this AD: Within 400 flight 
cycles after the effective date of this AD.

[[Page 93804]]

(i) Reporting

    At the applicable time specified in paragraph (i)(1) or (i)(2) 
of this AD, report the findings (both positive and negative) of the 
clearance check and detailed inspection required by paragraphs 
(g)(1) and (g)(2) of this AD, and each HFEC inspection required by 
paragraph (g)(3) of this AD. Send the report to Airbus at Airbus 
Service Bulletin Reporting Online Application on Airbus World 
(https://w3.airbus.com/), or in accordance with paragraph 7 of 
Airbus AOT A52W011-15, Revision 00, dated July 23, 2015. The report 
must include the applicable information specified in Appendix 2 of 
Airbus AOT A52W011-15, Revision 00, dated July 23, 2015.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 60 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 60 days after the effective date of 
this AD.

(j) Post-Repair Provisions

    (1) Accomplishment of corrective actions required by this AD 
does not terminate the repetitive HFEC inspections required by 
paragraph (g)(3) of this AD.
    (2) If all frame forks are replaced at the same time on the aft 
LDCD of an airplane, the next HFEC inspection required by paragraph 
(g)(3) of this AD can be deferred up to 4,500 flight cycles after 
the frame fork replacement.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. Information may be 
emailed to: [email protected]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; 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) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(l) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
European Airworthiness Directive 2015-0152, dated July 24, 2015, 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-2016-6894.

(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 Alert Operators Transmission A52W011-15, Revision 00, 
dated July 23, 2015, including the following appendices:
    (A) Appendix 1--Flowchart, undated.
    (B) Appendix 2--Reporting Sheet, undated. (None of the pages of 
Appendix 2 are numbered.)
    (C) Appendix 3--titled ``Technical Disposition,'' Ref. TD/K12/
L3/02978/2015, Issue B, dated July 21, 2015. (Appendix 3 is 
identified with an appendix number only on page 1 of Airbus Alert 
Operators Transmission A52W011-15, Revision 00, dated July 23, 
2015.)
    (D) Appendix 4--P/N identification for frame forks and bushings, 
undated.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email [email protected]; 
Internet http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on December 7, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-30031 Filed 12-21-16; 8:45 am]
 BILLING CODE 4910-13-P

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