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[Federal Register Volume 80, Number 239 (Monday, December 14, 2015)]
[Proposed Rules]
[Pages 77279-77283]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-31306]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-6550; Directorate Identifier 2013-NM-162-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) 90-11-05 
for certain Airbus Model A300 series airplanes and Model A300 B4-600 
series airplanes. AD 90-11-05 currently requires repetitive detailed 
inspections for cracking in the aft hinge brackets of the outer shroud 
box that is located in the outer wing box, and related investigative 
and corrective actions if necessary. Since we issued AD 90-11-05, we 
have determined that a change to certain compliance times is needed. 
This proposed AD would continue to require doing repetitive detailed 
inspections for cracking in the hinge brackets of the forward and aft 
outer shroud boxes that are located in the outer wing box, and related 
investigative and corrective actions if necessary; and would add 
airplanes to the applicability. We are proposing this AD to detect and 
correct cracking of the aft hinge brackets of the outer shroud box; 
such cracking could affect the structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by January 28, 
2016.

ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36

[[Page 77280]]

96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
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.

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-2015-
6550; 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 proposed AD, 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 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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-6550; 
Directorate Identifier 2013-NM-162-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

    On May 4, 1990, we issued AD 90-11-05, Amendment 39-6603 (55 FR 
20129, May 15, 1990). AD 90-11-05 requires actions intended to address 
an unsafe condition on certain Airbus Model A300 series airplanes and 
Model A300 B4-600 series airplanes.
    Since we issued AD 90-11-05, Amendment 39-6603 (55 FR 20129, May 
15, 1990), we have determined that a change to certain compliance times 
is needed.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0818R1, dated August 20, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Model A300 
series airplanes and Model A300 B4-600 series airplanes. The MCAI 
states:

    In the past, aft hinge brackets of the outer wing box were found 
cracked. Fracture of a bracket would allow vertical movement of the 
inner shroud box structure, which could result in damage to the top 
skin of the inboard flap. In addition, the loads carried by the 
brackets will be transferred to the remaining supports, which may 
also crack and cause extensive structural damage.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    To address this potential unsafe condition, DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 1998-
449-265(B) (later revised) to require repetitive inspections of the 
hinge bracket of the outer box and, depending on findings, 
corrective action(s).
    Since that [DGAC] AD was issued, a fleet survey and updated 
Fatigue and Damage Tolerance analysis were performed in order to 
substantiate the A300 Extended Service Goal (ESG) and A300-600 
Extended Service Goal (ESG2) exercise.
    The results of these analyses led to a change in the inspection 
thresholds and intervals in Flight Cycles (FC) and the introduction 
of Flight Hours (FH) limits.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD 1998-449-265(B)R1, which is 
superseded, but requires those actions within the new thresholds and 
intervals given by Airbus Service Bulletin (SB) A300-57-0142 
Revision 04 or A300-57-6010 Revision 05, as applicable to aeroplane 
model.
    Revision 1 of this [EASA] AD is issued to add model A300B4-203 
aeroplanes to the applicability and compliance time tables. This 
model is covered by Airbus SB A300-57-0142, but was mistakenly 
omitted from the original [EASA] AD issue.

    The corrective action for a hinge bracket that is cracked or 
fractured is replacing the damaged hinge bracket with a new bracket.
    For airplanes on which a crack is found in one half bracket or both 
half brackets, related investigative actions include a general visual 
inspection for secondary damage (e.g., cracks, wear damage, pitting, 
and gouging) in the following areas:
     The inner shroud-box forward attachments and the 
attachment brackets at the inboard end.
     The inner and outer shroud-box structure, adjacent to the 
fractured bracket.
     The top skin of the inboard flap.
    The corrective action for damage findings during the related 
investigative action is repair using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; or 
EASA; or Airbus's EASA Design Organization Approval (DOA).
    The compliance time for related investigative actions and 
corrective actions is before further flight.
    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-2015-
6550.

Related Service Information Under 1 CFR Part 51

    We reviewed the following service information.
     Airbus Service Bulletin A300-57-0142, Revision 04, dated 
March 30, 2011, which describes procedures for doing an inspection of 
the forward and aft hinge brackets on the outer shroud box.
     Airbus Service Bulletin A300-57-6010, Revision 05, dated 
February 21, 2011, which describes procedures for doing an inspection 
of the forward and aft hinge brackets on the outer shroud box.
     Airbus Service Bulletin A300-57-6011, Revision 2, dated 
July 10, 1989, which describes procedures for replacing the aft 
aluminum alloy brackets on the outer shroud box with new steel 
brackets.
    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 of this 
NPRM.

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.

[[Page 77281]]

Differences Between This Proposed AD and the MCAI or Service 
Information

    Although the MCAI or service information allows further flight 
after cracks are found during compliance with the required action, 
paragraph (g) of this proposed AD would require replacement of any 
cracked hinge bracket of the outer shroud box before further flight. 
This replacement before further flight is due to the safety 
implications and consequences of such cracking.

Costs of Compliance

    We estimate that this proposed AD affects 3 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                      Labor cost          Parts cost    Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection......................  8 work-hours x $85 per             $0   $680 per            $2,040 per
                                   hour = $680 per                         inspection cycle.   inspection cycle.
                                   inspection cycle.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                      Cost per
                    Action                                   Labor cost                Parts cost      product
----------------------------------------------------------------------------------------------------------------
Replacement..................................  27 work-hours x $85 per hour = $2,295      $25,650       $27,945
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition related investigative and 
corrective actions specified in this proposed AD.

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 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) 
90-11-05, Amendment 39-6603 (55 FR 20129, May 15, 1990), and adding the 
following new AD:

Airbus: Docket No. FAA-2015-6550; Directorate Identifier 2013-NM-
162-AD.

(a) Comments Due Date

    We must receive comments by January 28, 2016.

(b) Affected ADs

    This AD replaces AD 90-11-05, Amendment 39-6603 (55 FR 20129, 
May 15, 1990).

(c) Applicability

    This AD applies to Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-
2C, B4-103, and B4-203 airplanes; Model A300 B4-601, B4-603, B4-620, 
and B4-622 airplanes; and Model A300 B4-605R airplanes; certificated 
in any category; except airplanes on which Airbus Modification 
Number 6661 has been embodied during production.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by reports of cracks in the aft hinge 
brackets of the outer shroud box that is located in the outer wing 
box, which were found during routine maintenance checks, and our 
subsequent determination that a change in inspection compliance 
times is needed. We are issuing this AD to detect and correct 
cracking of the aft hinge brackets of the outer shroud box; such 
cracking could affect the structural integrity of the airplane.

(f) Compliance

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

(g) Repetitive Inspections

    At the applicable compliance time specified in paragraph (g)(1), 
(g)(2), or (g)(3) of this AD: Do a detailed inspection for cracks 
and fractures of the hinge brackets of the forward and aft outer 
shroud boxes, in

[[Page 77282]]

accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-0142, Revision 04, dated March 30, 2011; or Airbus 
Service Bulletin A300-57-6010, Revision 05, dated February 21, 2011; 
as applicable. Repeat the inspection thereafter at the applicable 
interval specified in paragraph (g)(1), (g)(2), or (g)(3) of this 
AD, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A300-57-0142, Revision 04, dated March 30, 2011; or 
Airbus Service Bulletin A300-57-6010, Revision 05, dated February 
21, 2011; as applicable. Doing the replacement specified in 
paragraph (j) of this AD terminates the repetitive inspections 
required by this paragraph.
    (1) For Model A300B4-601, B4-603, B4-605R, B4-620, B4-622, B4-
2C, and B4-203 airplanes: Do the inspection at the later of the 
times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. 
Repeat the inspection thereafter at intervals not to exceed 1,000 
flight cycles or 2,000 flight hours, whichever occurs first.
    (i) Before the accumulation of 5,000 flight cycles or 10,400 
flight hours since first flight, whichever occurs first.
    (ii) Within 100 flight cycles after the effective date of this 
AD.
    (2) For Model A300B2-1C, B2-203, and B2K-3C airplanes: Do the 
inspection at the later of the times specified in paragraphs 
(g)(2)(i) and (g)(2)(ii) of this AD. Repeat the inspection 
thereafter at intervals not to exceed 1,000 flight cycles or 1,000 
flight hours, whichever occurs first.
    (i) Before the accumulation of 5,000 flight cycles or 5,400 
flight hours since first flight, whichever occurs first.
    (ii) Within 100 flight cycles after the effective date of this 
AD.
    (3) For Model A300B4-103 airplanes: Do the inspection the later 
of the times specified in paragraphs (g)(3)(i) and (g)(3)(ii) of 
this AD. Repeat the inspection thereafter at intervals not to exceed 
1,000 flight cycles or 1,300 flight hours, whichever occurs first.
    (i) Before the accumulation of 5,000 flight cycles or 6,600 
flight hours since first flight, whichever occurs first.
    (ii) Within 100 flight cycles after the effective date of this 
AD.

(h) Corrective Action

    If any crack or fracture is found during any inspection required 
by paragraph (g) of this AD: Before further flight, replace the 
damaged hinge bracket with a new bracket, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-143, 
Revision 2, dated July 10, 1989 (for Model A300 series airplanes); 
or A300-57-6011, Revision 2, dated July 10, 1989 (for Model A300 B4-
600 series airplanes); as applicable.

(i) Related Investigative and Corrective Actions

    If any crack or fracture is found during any inspection required 
by paragraph (g) of this AD: Before further flight, do a general 
visual inspection for secondary damage (e.g., cracks, wear damage, 
pitting, and gouging) in the areas specified in paragraphs (i)(1), 
(i)(2), and (i)(3) of this AD, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-0142, Revision 04, 
dated March 30, 2011; or Airbus Service Bulletin A300-57-6010, 
Revision 05, dated February 21, 2011; as applicable. If any damage 
is found, before further flight, repair using a method approved by 
the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA; or Airbus's EASA Design Organization 
Approval (DOA).
    (1) The inner shroud-box forward attachments and the attachment 
brackets at the inboard end.
    (2) The inner and outer shroud-box structure, adjacent to the 
fractured bracket.
    (3) The top skin of the inboard flap.

(j) Optional Terminating Action for Inspection Requirements of 
Paragraph (g) of this AD

    (1) Replacement of the hinge bracket, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-143, 
Revision 2, dated July 10, 1989 (for Model A300 series airplanes); 
or A300-57-6011, Revision 2, dated July 10, 1989 (for Model A300 B4-
600 series airplanes); as applicable, terminates the inspection 
requirements of paragraph (g) of this AD.
    (2) Replacement of a hinge bracket before the effective date of 
this AD, as described in the applicable service information listed 
in paragraphs (j)(2)(i) through (j)(2)(iv) of this AD, terminates 
the repetitive inspections required by paragraph (g) of this AD, 
provided that after the hinge bracket replacement, but before 
further flight after the effective date of this AD, a one-time 
detailed inspection of the forward and aft outer shroud box has been 
done with no cracking found, in accordance with paragraph (g) of 
this AD. The following service information is not incorporated by 
reference in this AD.
    (i) Airbus Service Bulletin A300-57-143, dated December 17, 
1986.
    (ii) Airbus Service Bulletin A300-57-143, Revision 1, dated 
March 19, 1987.
    (iii) Airbus Service Bulletin A300-57-6011, dated December 17, 
1986.
    (iv) Airbus Service Bulletin A300-57-6011, Revision 1, dated 
March 19, 1987.

(k) Credit for Previous Actions

    (1) This paragraph provides credit for inspections required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using any of the applicable service 
information listed in paragraphs (k)(1)(i) through (k)(1)(viii) of 
this AD, which are not incorporated by reference in this AD.
    (i) Airbus Service Bulletin A300-57-142, dated December 17, 
1986.
    (ii) Airbus Service Bulletin A300-57-142, Revision 1, dated 
April 9, 1990.
    (iii) Airbus Service Bulletin A300-57-142, Revision 2, dated 
January 16, 1991.
    (iv) Airbus Service Bulletin A300-57-0142, Revision 03, dated 
February 22, 1999.
    (v) Airbus Service Bulletin A300-57-6010, Revision 1, dated 
December 14, 1990.
    (vi) Airbus Service Bulletin A300-57-6010, Revision 02, dated 
March 30, 1998.
    (vii) Airbus Service Bulletin A300-57-6010, Revision 03, dated 
September 16, 1998.
    (viii) Airbus Service Bulletin A300-57-6010, Revision 04, dated 
February 22, 1999.
    (2) This paragraph provides credit for replacement of the hinge 
bracket as specified in paragraph (j)(2) of this AD, if the 
replacement was performed before the effective date of this AD, 
using any of the applicable service information listed in paragraphs 
(k)(2)(i) through (k)(2)(iv) of this AD, which is not incorporated 
by reference in this AD.
    (i) Airbus Service Bulletin A300-57-143, dated December 17, 
1986.
    (ii) Airbus Service Bulletin A300-57-143, Revision 1, dated 
March 19, 1987.
    (iii) Airbus Service Bulletin A300-57-6011, dated December 17, 
1986.
    (iv) Airbus Service Bulletin A300-57-6011, Revision 1, dated 
March 19, 1987.

(l) 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: 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. The 
AMOC approval letter must specifically reference this AD.
    (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 Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0181R1, dated August 20, 
2013, 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-2015-6550.
    (2) 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. You may view this referenced service 
information at the FAA, Transport Airplane

[[Page 77283]]

Directorate, 1601 Lind Avenue SW., Renton, WA. For information on 
the availability of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on December 4, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-31306 Filed 12-11-15; 8:45 am]
 BILLING CODE 4910-13-P
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