Document ID: FAA-2018-0417-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2018-05-25T04:00Z

[Federal Register Volume 83, Number 102 (Friday, May 25, 2018)]
[Proposed Rules]
[Pages 24244-24248]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-11134]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0417; Product Identifier 2017-NM-132-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2016-25-
03, which applies to certain Airbus Model A300 F4-600R series 
airplanes. AD 2016-25-03 requires repetitive high frequency eddy 
current (HFEC) inspections of the aft lower deck cargo door (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. Since we issued AD 2016-25-03, we have 
determined that accomplishing a new frame fork repair or reinforcement 
would allow an extension of the repetitive inspection intervals as 
would a frame fork replacement. This proposed AD would retain the 
actions required by AD 2016-25-03, with revised corrective actions and 
compliance times. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by July 9, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

[[Page 24245]]

    For service information identified in this NPRM, 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, 2200 South 216th St., Des Moines, WA. 
For information on the availability of this material at the FAA, call 
206-231-3195.

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-2018-
0417; 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 NPRM, the regulatory evaluation, any comments received, 
and other information. The street address for the Docket Operations 
office (telephone 800-647-5527) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3225.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2018-0417; 
Product Identifier 2017-NM-132-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this proposed AD. We will consider 
all comments received by the closing date and may amend this proposed 
AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We issued AD 2016-25-03, Amendment 39-18729 (81 FR 93801, December 
22, 2016) (``AD 2016-25-03''), for certain Airbus Model A300 F4-600R 
series airplanes. AD 2016-25-03 requires 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. AD 2016-25-03 resulted 
from a report of two adjacent frame forks that were found cracked on 
the aft LDCD of two Model A300-600F4 airplanes during scheduled 
maintenance. We issued AD 2016-25-03 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.

Actions Since AD 2016-25-03 Was Issued

    Since we issued AD 2016-25-03, we have determined that 
accomplishing a new frame fork repair or reinforcement would allow an 
extension of the repetitive inspection intervals as would the existing 
frame fork replacement.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0152R1, dated May 23, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A300 F4-600R series 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, 
and, consequently, EASA issued AD 2015-0152 [which corresponds to 
FAA AD 2016-25-03] to require repetitive inspections of the aft LDCD 
frame forks and, depending on findings, the accomplishment of 
applicable corrective action(s).
    Since that AD was issued, Airbus published Service Bulletin (SB) 
SB A300-52-6085 which provides frame fork reinforcement instruction 
and SB A300-52-6086 which provides instruction to inspect the cargo 
door for cracks as well as frame fork replacement instructions 
having the inspection interval extended from 600 flight cycles (FC) 
to 1,200 FC.
    For the reason described above, this [EASA] AD is revised to 
introduce frame forks replacement or repair [or reinforcement] as an 
allowance to extend the inspection interval.

    Required actions include repetitive HFEC inspections of the aft 
LDCD frame forks and repair, reinforcement, or replacement if 
necessary; a one-time check of the LDCD clearances and adjustment if 
necessary; and a one-time detailed visual inspection of hooks, 
eccentric bushes, and x-stops for wear, and corrective actions if 
necessary. Corrective actions include blend-out, adjustment, and 
replacement of hooks, bushes and x-stops. 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-2018-0417.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:
     Alert Operators Transmission--AOT A52W011-15, Revision 00, 
dated July 23, 2015, which describes procedures for a check of the aft 
LDCD clearances ``U'' and ``V'' between the latching hooks and the 
eccentric bush at frame (FR)60 through FR64A and an adjustment of the 
latching hook; a detailed inspection to detect signs of wear of the 
hooks, eccentric bushes, and x-stops and corrective actions; and an 
HFEC inspection to detect cracking at all frame fork stations of the 
aft LDCD and a replacement of the frame fork.
     Service Bulletin A300-52-6085, Revision 00, dated December 
22, 2016. This service information describes procedures for reinforcing 
frame fork fastener holes, which include related investigative and 
corrective actions. The related investigative actions include a 
rotating probe inspection for cracking of the fastener holes and a 
check to determine the hole diameter. Corrective actions include repair 
and cold working the fastener holes.
     Service Bulletin A300-52-6086, Revision 00, dated December 
25, 2016, which describes procedures for a check of the aft LDCD 
clearances ``U'' and ``V'' between the latching hooks and the eccentric 
bush at FR60 through FR64A and an adjustment of the latching hook; and 
HFEC inspection to detect cracking at all frame fork stations of the 
aft LDCD and a repair of the frame fork.
    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.

[[Page 24246]]

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Costs of Compliance

    We estimate that this proposed AD affects 58 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
17 work-hours x $85 per hour = $1,445........................              $0           $1,445          $83,810
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary on-condition 
actions that would be required based on the results of any required 
actions. We have no way of determining the number of aircraft that 
might need these on-condition actions:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
Up to 65 work-hours x $85 per hour =           $10,000          $15,525
 $5,525...............................
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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 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This proposed 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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 removing Airworthiness Directive (AD) 
2016-25-03, Amendment 39-18729 (81 FR 93801, December 22, 2016), and 
adding the following new AD:

Airbus: Docket No. FAA-2018-0417; Product Identifier 2017-NM-132-AD.

(a) Comments Due Date

    We must receive comments by July 9, 2018.

(b) Affected ADs

    This AD replaces AD 2016-25-03, Amendment 39-18729 (81 FR 93801, 
December 22, 2016) (``AD 2016-25-03'').

(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 airplanes during scheduled maintenance, and the introduction of 
frame fork

[[Page 24247]]

reinforcement or repair procedures that, when done, allow an 
extension of repetitive inspection intervals. We are issuing this AD 
to address 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) Retained Inspection Requirements and On-Condition Actions, With 
Revised Compliance Times and New Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2016-25-03, with revised compliance times and new service 
information. At the applicable time specified in paragraph (h) of 
this AD, or before exceeding the threshold defined in table 1 to 
paragraph (g) of this AD, whichever occurs later: Do the actions 
specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 
Repeat the high frequency eddy current (HFEC) inspection specified 
in paragraph (g)(3) of this AD thereafter at intervals not to exceed 
the applicable times specified in table 1 to paragraph (g) of this 
AD.
    (1) A one-time check of the aft LDCD clearances ``U'' and ``V'' 
between the latching hooks and the eccentric bush at FR60 through 
FR64A, in accordance with the instructions of Airbus Alert Operators 
Transmission--AOT A52W011-15, Revision 00, dated July 23, 2015; or 
the Accomplishment Instructions of Airbus Service Bulletin A300-52-
6086, Revision 00, dated December 25, 2016. If any value outside 
tolerance is found, adjust the latching hook before further flight, 
in accordance with the instructions of Airbus Alert Operators 
Transmission--AOT A52W011-15, Revision 00, dated July 23, 2015; or 
the Accomplishment Instructions of Airbus Service Bulletin A300-52-
6086, Revision 00, dated December 25, 2016.
    (2) A one-time detailed inspection to detect signs of wear of 
the hooks, eccentric bushes, and x-stops, in accordance with the 
instructions of Airbus Alert Operators Transmission--AOT A52W011-15, 
Revision 00, dated July 23, 2015. If any wear is found, do all 
applicable corrective actions before further flight, in accordance 
with the instructions of Airbus Alert Operators Transmission--AOT 
A52W011-15, Revision 00, dated July 23, 2015.
    (3) An HFEC inspection to detect cracking at all frame fork 
stations of the aft LDCD, in accordance with the instructions of 
Airbus Alert Operators Transmission--AOT A52W011-15, Revision 00, 
dated July 23, 2015; or the Accomplishment Instructions of Airbus 
Service Bulletin A300-52-6086, Revision 00, dated December 25, 2016. 
If any crack is found, before further flight, replace the cracked 
frame fork, in accordance with the instructions of Airbus Alert 
Operators Transmission--AOT A52W011-15, Revision 00, dated July 23, 
2015; repair the cracked frame fork, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-52-6086, 
Revision 00, dated December 25, 2016; or reinforce the cracked frame 
fork, including doing all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-52-6085, Revision 00, 
dated December 22, 2016, except as required by paragraph (i) of this 
AD.
[GRAPHIC] [TIFF OMITTED] TP25MY18.000

(h) Retained Compliance Times, With No Changes

    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 January 26, 2017 (the effective date of AD 2016-
25-03): Within 100 flight cycles after January 26, 2017.
    (ii) For airplanes that have accumulated fewer than 8,000 total 
flight cycles as of January 26, 2017 (the effective date of AD 2016-
25-03): Within 400 flight cycles after January 26, 2017.

(i) Service Information Exception

    Where Airbus Service Bulletin A300-52-6085, Revision 00, dated 
December 22, 2016, specifies to contact Airbus for appropriate 
action: Before further flight, accomplish corrective actions in 
accordance with the procedures specified in paragraph (m)(2) of this 
AD.

(j) No Terminating Action

    Accomplishment of corrective actions on an airplane as required 
by paragraph (g)(1) or (g)(2) of this AD, or repair, reinforcement, 
or replacement of a frame fork as required by paragraph (g)(3) of 
this AD, on the aft LDCD of an airplane does not constitute 
terminating action for the repetitive HFEC inspections required by 
paragraph (g)(3) of this AD for that airplane.

(k) Compliance Time Clarification

    After replacement, repair, or reinforcement of any frame fork on 
the aft LDCD of an airplane, as specified in paragraph (g)(3) of 
this AD, the next HFEC inspection as required by paragraph (g)(3) of 
this AD can be deferred for any frame fork that is replaced, 
repaired, or reinforced, but must be accomplished before exceeding 
6,800 flight cycles after the replacement, repair, or reinforcement 
of that frame fork.

(l) No Reporting

    Although the Accomplishment Instructions of Airbus Alert 
Operators Transmission--AOT A52W011-15, Revision 00, dated July 23, 
2015; and Airbus Service Bulletin A300-52-6086, Revision 00, dated 
December 25, 2016, specify to submit certain information to

[[Page 24248]]

the manufacturer, this AD does not include that requirement.

(m) Other FAA AD Provisions

    (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 (n)(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: As of the effective date of 
this AD, 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): Except as required by 
paragraph (i) and paragraph (l) of this AD: 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.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2015-0152R1, dated May 23, 2017, 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-2018-0417.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3225.
    (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. You may view this service 
information at the FAA, Transport Standards Branch, 2200 South 216th 
St., Des Moines, WA. For information on the availability of this 
material at the FAA, call 206-231-3195.

    Issued in Des Moines, Washington, on May 11, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-11134 Filed 5-24-18; 8:45 am]
 BILLING CODE 4910-13-P