[Federal Register Volume 82, Number 143 (Thursday, July 27, 2017)]
[Proposed Rules]
[Pages 34885-34888]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-15558]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0710; Directorate Identifier 2017-NM-019-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 adopt a new airworthiness directive (AD) for 
certain Airbus Model A300 B4-600R series airplanes; Model A300 B4-603, 
B4-620, and B4-622 airplanes; Model A300 C4-605R Variant F airplanes; 
and Model A300 F4-605R airplanes. This proposed AD was prompted by a 
determination that the top stringer joints at rib 18 are an area of 
uniform stress distribution, which indicates that cracks may develop in 
adjacent stringers at the same time. This proposed AD would require an 
inspection of the upper wing skin and top stringer joints, and 
modification of the stringer joint couplings if necessary. We are 
proposing this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by September 11, 
2017.

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-

[[Page 34886]]

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.
    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 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-2017-
0710; 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 proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-0710; 
Directorate Identifier 2017-NM-019-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

    Fatigue damage can occur locally, in small areas or structural 
design details, or globally, in widespread areas. Multiple-site damage 
is widespread damage that occurs in a large structural element such as 
a single rivet line of a lap splice joining two large skin panels. 
Widespread damage can also occur in multiple elements such as adjacent 
frames or stringers. Multiple-site damage and multiple-element damage 
cracks are typically too small initially to be reliably detected with 
normal inspection methods. Without intervention, these cracks will 
grow, and eventually compromise the structural integrity of the 
airplane. This condition is known as widespread fatigue damage (WFD). 
It is associated with general degradation of large areas of structure 
with similar structural details and stress levels. As an airplane ages, 
WFD will likely occur, and will certainly occur if the airplane is 
operated long enough without any intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all of these 
airplanes that will be certificated in the future. For existing and 
future airplanes subject to the WFD rule, the rule requires that DAHs 
establish a limit of validity (LOV) of the engineering data that 
support the structural maintenance program. Operators affected by the 
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV 
is approved.
    The WFD rule (75 FR 69746, November 15, 2010) does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions necessary to reach the LOV will be mandated by airworthiness 
directives through separate rulemaking actions.
    In the context of WFD, this action is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur. This 
approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2017-0023, dated February 10, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A300 B4-600R series airplanes; Model A300 B4-603, B4-620, and B4-622 
airplanes; Model A300 C4-605R Variant F airplanes; and Model A300 F4-
605R airplanes. The MCAI states:

    In response to the FAA Part 26 rule change concerning Widespread 
Fatigue Damage (WFD), all wing structural items of the A300-600 
design deemed potentially susceptible to WFD were assessed. The top 
stringer joints at Rib 18 were highlighted as an area of uniform 
stress distribution, indicating that cracks may develop in adjacent 
stringers at the same time which is known as Multi Element Damage 
(MED). Each affected stringer joint consists of three main load 
transferring parts: An overlapping flange, two straps attached 
through the stringer web and a strap on the top flange. All the 
components of the joint are attached with fasteners. The fastener 
holes were the subject of a MED WFD analysis, which showed that 
cracking could occur from a number of the holes in the joint on 
stringers 11, 12, 13, 14, 15, 16, 17, and 18.
    This condition, if not detected and corrected, could reduce the 
structural integrity of the wing.
    Prompted by the conclusion of the WFD analysis, Airbus issued 
Service Bulletin (SB) A300-57-6118 to provide modification 
instructions. The modification will both re-life via oversizing and 
inspect via non-destructive test a defined number of stringer joint 
fastener holes at Rib 18. This modification will delay the onset of 
cracking at the stringer joint, providing it is completed at the 
specified time and will delay the requirement for subsequent 
inspection.
    For the reasons described above, this [EASA] AD requires a 
detailed visual inspection (DVI) [for damage, including cracking] of 
the upper wing skin and the top stringer joints at Rib 18, [and 
corrective action if necessary] and modification of the stringer 
joint couplings at Rib 18, on both wings [as applicable].

    The modification includes a related investigative action, i.e., a 
special detailed (roto-probe) inspection for damage, including 
cracking, of the fastener holes in the upper wing skin, and corrective 
action if necessary. Corrective actions include repairing any damage. 
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-2017-
0710.

[[Page 34887]]

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-57-6118, Revision 01, dated 
January 31, 2017. This service information describes procedures for an 
inspection of the upper wing skin and top stringer joints at rib 18, 
and modification of the stringer joint couplings. 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.

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

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspections and modification..........  37 work-hours x $85 per           $4,770          $7,915        $514,475
                                         hour = $3,145.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition 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 adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2017-0710; Directorate Identifier 2017-NM-
019-AD.

(a) Comments Due Date

    We must receive comments by September 11, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A300 B4-605R, B4-622R, B4-603, 
C4-605R Variant F, B4-620, B4-622, and F4-605R airplanes, 
certificated in any category, all serial numbers except Model A300 
F4-605R airplanes that have embodied Airbus modification 12699 in 
production.

(d) Subject

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

(e) Reason

    This AD was prompted by a determination that the top stringer 
joints at rib 18 are an area of uniform stress distribution, which 
indicates that cracks may develop in adjacent stringers at the same 
time. We are issuing this AD to detect and correct damage (including 
cracking) at the stringer joints, which could reduce the structural 
integrity of the wing.

(f) Compliance

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

(g) Definitions

    For the purposes of this AD, the definitions in paragraphs 
(g)(1) through (g)(5) of this AD apply.
    (1) Group 1 airplanes are defined as Airbus Model A300 B4-603, 
B4-605R, B4-620, B4-622, and B4-622R airplanes.
    (2) Group 2 airplanes are defined as Airbus Model A300 C4-605 
Variant F and F4-605R (if in pre-modification 12699 configuration) 
airplanes.
    (3) Short range (SR) is defined as airplanes with an average 
flight time of less than 1.5 flight hours per flight cycle.
    (4) Long range (LR) is defined as airplanes with an average 
flight time equal to or higher than 1.5 flight hours per flight 
cycle.
    (5) For determining the ``short range'' and ``long range'' 
airplanes, the average flight time is the total accumulated flight 
hours, counted from take-off to touch-down, divided by the total 
accumulated flight cycles at the effective date of this AD.

(h) Inspection and Modification

    Not before exceeding the applicable lower thresholds as 
specified in table 1 to paragraph (h) of this AD, and within the 
compliance times specified in paragraphs (h)(1), (h)(2), (h)(3), and 
(h)(4) of this AD, as applicable: Accomplish a detailed visual

[[Page 34888]]

inspection for damage (including cracking) of the upper wing skin 
and top stringer joints at rib 18 on both wings, do all applicable 
corrective actions, and do the applicable modification, including 
related investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6118, 
Revision 01, dated January 31, 2017, except as required by paragraph 
(i) of this AD. Do all applicable modifications, related 
investigative actions, and corrective actions before further flight.
    (1) For Group 1, LR airplanes: Inspect at the time specified in 
paragraph (h)(1)(i) or (h)(1)(ii) of this AD, whichever occurs 
later.
    (i) Before exceeding 32,500 flight cycles or 70,300 flight 
hours, whichever occurs first since first flight of the airplane.
    (ii) Within 700 flight cycles, 1,500 flight hours, or 12 months, 
whichever occurs first after the effective date of this AD.
    (2) For Group 1, SR airplanes: Inspect at the time specified in 
paragraphs (h)(2)(i) or (h)(2)(ii) of this AD, whichever occurs 
later.
    (i) Before exceeding 35,100 flight cycles or 52,600 flight 
hours, whichever occurs first since the first flight of the 
airplane.
    (ii) Within 700 flight cycles or 1,000 flight hours, or 12 
months, whichever occurs first after the effective date of this AD.
    (3) For Group 2, LR airplanes: Inspect before exceeding 35,000 
flight cycles or 75,700 flight hours, whichever occurs first since 
the first flight of the airplane.
    (4) For Group 2, SR airplanes: Inspect before exceeding 37,800 
flight cycles or 56,700 flight hours, whichever occurs first since 
the first flight of the airplane.

  Table 1 to Paragraph (h) of This AD--Compliance Time Lower Thresholds
------------------------------------------------------------------------
                                     Compliance time flight cycles (FC)
                                       or flight hours (FH), whichever
       Applicable  airplanes         occurs first since first flight of
                                                the airplane
------------------------------------------------------------------------
Group 1, LR.......................  Not before exceeding 30,900 FC or
                                     66,700 FH.
Group 1, SR.......................  Not before exceeding 28,700 FC or
                                     43,000 FH.
Group 2, LR.......................  Not before exceeding 28,600 FC or
                                     61,700 FH.
Group 2, SR.......................  Not before exceeding 34,400 FC or
                                     51,600 FH.
------------------------------------------------------------------------

(i) Service Information Exception

    Where Airbus Service Bulletin A300-57-6118, Revision 01, dated 
January 31, 2017, specifies to contact Airbus for appropriate 
action, and specifies that action as ``RC'' (Required for 
Compliance): Before further flight, accomplish corrective actions in 
accordance with the procedures specified in paragraph (k)(2) of this 
AD.

(j) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(h) of this AD, if those actions were performed before the effective 
date of this AD using Airbus Service Bulletin A300-57-6118, dated 
June 30, 2015.

(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, 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 manager of the 
International Branch, send it to the attention of the person 
identified in paragraph (l)(2) of this AD. Information may be 
emailed to: [email protected]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
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) 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 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 2017-0023, dated February 10, 
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-2017-0710.
    (2) For more information about this AD, 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.
    (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 Airplane 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 July 18, 2017.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-15558 Filed 7-26-17; 8:45 am]
BILLING CODE 4910-13-P