81_FR_44362 81 FR 44232 - Airworthiness Directives; Airbus Airplanes

81 FR 44232 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 130 (July 7, 2016)

Page Range44232-44235
FR Document2016-15910

We propose to supersede Airworthiness Directive (AD) 2011-17- 05, for certain Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C airplanes. AD 2011-17-05 currently requires repetitive inspections in sections 13 through 18 of the fuselage between rivets of the longitudinal lap joints between frames (FR) 18 and 80 for cracking, and repair or modification if necessary. Since we issued AD 2011-17-05, we have determined that a revised inspection program is necessary. This proposed AD would include a revised repetitive inspection program of all longitudinal lap joints and repairs between frames 18 and 80 to address this widespread fatigue damage (WFD). We are proposing this AD to detect and correct fatigue cracking of the longitudinal lap joints of the fuselage, which could result in reduced structural integrity of the airplane.

Federal Register, Volume 81 Issue 130 (Thursday, July 7, 2016)
[Federal Register Volume 81, Number 130 (Thursday, July 7, 2016)]
[Proposed Rules]
[Pages 44232-44235]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-15910]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 81, No. 130 / Thursday, July 7, 2016 / 
Proposed Rules

[[Page 44232]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-7425; Directorate Identifier 2014-NM-244-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2011-17-
05, for certain Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, 
A300-B4-103, A300 B4-203, and A300 B4-2C airplanes. AD 2011-17-05 
currently requires repetitive inspections in sections 13 through 18 of 
the fuselage between rivets of the longitudinal lap joints between 
frames (FR) 18 and 80 for cracking, and repair or modification if 
necessary. Since we issued AD 2011-17-05, we have determined that a 
revised inspection program is necessary. This proposed AD would include 
a revised repetitive inspection program of all longitudinal lap joints 
and repairs between frames 18 and 80 to address this widespread fatigue 
damage (WFD). We are proposing this AD to detect and correct fatigue 
cracking of the longitudinal lap joints of the fuselage, which could 
result in reduced structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by August 22, 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 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-2016-
7425; 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-2016-7425; 
Directorate Identifier 2014-NM-244-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 September 23, 2011, we issued AD 2011-17-05, Amendment 39-16769 
(76 FR 63177, October 12, 2011) (``AD 2011-17-05''). AD 2011-17-05 
requires actions intended to address an unsafe condition on certain 
Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-103, A300 
B4-203, and A300 B4-2C airplanes.
    Since we issued AD 2011-17-05, we have determined it is necessary 
to require a revised inspection program for the longitudinal lap joints 
and repairs between FR 18 and FR 80 because additional cracking was 
found in an expanded area.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0265, dated December 9, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    Cracks were found on in-service aeroplanes in sections 13 to 18 
of the fuselage between rivets of longitudinal lap joints between 
frames (FR) 18 and FR80.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    To address this unsafe condition, Airbus developed an inspection 
programme for the longitudinal lap joints and repairs between FR18 
and FR80, and EASA issued AD 2007-0091 [which corresponds to FAA AD 
2011-17-05] to require the implementation of that programme.
    Since EASA AD 2007-0091 was issued, [a] new Widespread Fatigue 
Damage regulation has been issued. This new regulation led to the 
revision of the maintenance programme for the longitudinal lap 
joints and repairs between FR18 and FR80.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2007-0091, which is superseded, and requires 
implementation of the revised inspection programme.

    Required actions include repetitive inspections of the bonded inner

[[Page 44233]]

doublers of the longitudinal lap joints in sections 13 through 18 for 
disbonding or corrosion, and repairing any disbonding and corrosion; a 
follow-on rototest or ultrasonic inspection to verify cracking, and 
repair of any cracking. The repetitive inspection interval ranges from 
3,000 flight cycles up to 8,000 flight cycles, depending on airplane 
configuration. You may examine the MCAI in the AD docket on the 
Internet at http://www.regulations.gov by searching for and locating it 
in Docket No. FAA-2016-7425.

Widespread Fatigue Damage

    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. 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.
    We are issuing this AD to detect and correct fatigue cracking of 
the longitudinal lap joints of the fuselage, which could result in 
reduced structural integrity of the airplane.

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.

Differences Between This Proposed AD and the MCAI or Service 
Information

    Unlike the procedures described in the service information, this 
proposed AD would not permit further flight if cracks are detected. We 
have determined that, because of the safety implications and 
consequences associated with that cracking, any cracked upper shell 
structure must be repaired before further flight.
    The MCAI refers to Airbus Service Bulletin A300-53-0211, Revision 
08, dated November 26, 2013, for compliance times and for the new 
inspections. However, paragraph (l) of this proposed AD would require 
operators to do the initial inspections within 180 days after the 
effective date of this AD, in 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); and thereafter at intervals approved by 
the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA; or Airbus's EASA DOA. We find that 180 days 
is an appropriate amount of time to accomplish the initial inspections 
and address the unsafe condition.
    These differences have been coordinated with the EASA and Airbus.

Costs of Compliance

    We estimate that this proposed AD affects 4 airplanes of U.S. 
registry.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                    Action                                 Labor cost                 product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2011-17-05 (5          3,735 work-hours x $85 per hour         $317,475      $1,587,375
 airplanes).                                     = $317,475.
New proposed inspections (4 airplanes)........  140 work-hours x $85 per hour =           11,900          47,600
                                                 $11,900.
----------------------------------------------------------------------------------------------------------------

    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.

[[Page 44234]]

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) 
2011-17-05, Amendment 39-16769 (76 FR 63177, October 12, 2011), and 
adding the following new AD:

Airbus: Docket No. FAA-2016-7425; Directorate Identifier 2014-NM-
244-AD.

(a) Comments Due Date

    We must receive comments by August 22, 2016.

(b) Affected ADs

    This AD replaces AD 2011-17-05, Amendment 39-16769 (76 FR 63177, 
October 12, 2011) (``AD 2011-17-05'').

(c) Applicability

    This AD applies to Airbus Model A300 B2-1C, A300 B2-203, A300 
B2K-3C, A300-B4-103, A300 B4-203, and A300 B4-2C airplanes; 
certificated in any category; all manufacturer serial numbers, 
except those on which Airbus Modification 2611 has been embodied in 
production.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by an evaluation done by the design 
approval holder indicating that certain sections of the longitudinal 
lap joints are subject to widespread fatigue damage. We are issuing 
this AD to detect and correct fatigue cracking of the longitudinal 
lap joints of the fuselage, which could result in reduced structural 
integrity of the airplane.

(f) Compliance

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

(g) Retained Fuselage Inner Doubler Inspections and Repair, With 
Revised Formatting

    This paragraph restates the requirements of paragraph (l) of AD 
2011-17-05, with revised formatting. For airplanes on which any 
inspections of the fuselage bonded inner doublers of the 
longitudinal lap joints in Sections 13 through 18 (except Sections 
16 and 17 at Stringer 31 left-hand and right-hand) for disbonding 
and cracking have not been done as of November 16, 2011 (the 
effective date of AD 2011-17-05), as specified by Airbus Service 
Bulletin A300-53-229: Prior to the accumulation of 24,000 total 
flight cycles or within 15 years since new, whichever occurs first; 
or within 60 days after November 16, 2011; whichever occurs later; 
do a detailed inspection of the fuselage bonded inner doublers of 
the longitudinal lap joints in Sections 13 through 18 (except 
Sections 16 and 17 at Stringer 31 left-hand and right-hand) for 
disbonding and cracking, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-229, Revision 5, 
dated April 8, 1997. If no disbonding and no cracking are found, 
repeat the inspection thereafter at the applicable intervals 
specified in paragraph (h) of this AD.
    (1) If no cracking is found, and ``minor'' disbonding, as 
defined in Airbus Service Bulletin A300-53-229, Revision 5, dated 
April 8, 1997, is found: Repeat the inspection thereafter at 
intervals not to exceed 1 year for areas below stringer 22, and at 
intervals not to exceed 2 years for areas above and including 
stringer 22.
    (2) If no cracking is found, and ``major'' disbonding, as 
defined in Airbus Service Bulletin A300-53-229, Revision 5, dated 
April 8, 1997, is found: Within 1,000 flight cycles after doing the 
inspection, repair, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-229, Revision 5, 
dated April 8, 1997.
    (3) If any cracking is found, repair prior to further flight, in 
accordance with Airbus Service Bulletin A300-53-229, Revision 5, 
dated April 8, 1997.

(h) Retained Repetitive Intervals for Inspections for Disbonding and 
Cracking

    This paragraph restates the repetitive intervals specified in 
table 1 of AD 2011-17-05. At the applicable time specified in 
paragraph (h)(1) or (h)(2) of this AD, repeat the inspection 
required by paragraph (g) of this AD.
    (1) For Sections 13 and 14 as specified in Airbus Service 
Bulletin A300-53-229, Revision 5, dated April 8, 1997: Repeat the 
inspection at intervals not to exceed 7 years or 12,000 flight 
cycles, whichever occurs first.
    (2) For Sections 15 through 18 as specified in Airbus Service 
Bulletin A300-53-229, Revision 5, dated April 8, 1997: Repeat the 
inspection within 8.5 years or 12,000 flight cycles, whichever 
occurs first.

(i) Retained Fuselage Inner Doubler Inspections and Repair

    This paragraph restates the requirements of paragraph (m) of AD 
2011-17-05. For airplanes on which any inspections of the fuselage 
bonded inner doublers of the longitudinal lap joints in Sections 13 
through 18 (except Sections 16 and 17 at Stringer 31 left-hand and 
right-hand) for disbonding and cracking have been done as of 
November 16, 2011 (the effective date of AD 2011-17-05), as 
specified in Airbus Service Bulletin A300-53-229; except for 
airplanes on which a repair of that area has been done as specified 
in Airbus Service Bulletin A300-53-229: Within 7 years or 12,000 
flight cycles (for Sections 13 and 14), or within 8.5 years or 
12,000 flight cycles (for Sections 15 and 18), after doing the 
inspection, whichever occurs first; or within 60 days after November 
16, 2011, whichever occurs later, do a detailed inspection of the 
fuselage bonded inner doublers of the longitudinal lap joints in 
Sections 13 through 18 (except Sections 16 and 17 at Stringer 31 
left-hand and right-hand) for disbonding and cracking, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A300-53-229, Revision 5, dated April 8, 1997. If no disbonding and 
no cracking are found, repeat the inspection at the applicable time 
specified in paragraph (h) of this AD.
    (1) If no cracking is found, and ``minor'' disbonding, as 
defined in Airbus Service Bulletin A300-53-229, Revision 5, dated 
April 8, 1997, is found: Repeat the inspection thereafter at 
intervals not to exceed 1 year for areas below stringer 22, and at 
intervals not to exceed 2 years for areas above and including 
stringer 22.
    (2) If no cracking is found, and ``major'' disbonding, as 
defined in Airbus Service Bulletin A300-53-229, Revision 5, dated 
April 8, 1997, is found: Within 1,000 flight cycles after doing the 
inspection, repair, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-229, Revision 5, 
dated April 8, 1997.
    (3) If any cracking is found, repair prior to further flight, in 
accordance with Airbus Service Bulletin A300-53-229, Revision 5, 
dated April 8, 1997.

(j) Retained Fuselage Inner Doubler Inspections and Repair, With No 
Changes

    This paragraph restates the requirements of paragraph (n) of AD 
2011-17-05, with no changes. For airplanes on which any inspections 
of the fuselage bonded inner doublers of the longitudinal lap joints 
in Sections 16 and 17 at Stringer 31 left-hand

[[Page 44235]]

and right-hand for disbonding and cracking have not been done as of 
November 16, 2011 (the effective date of AD 2011-17-05), as 
specified in Airbus Service Bulletin A300-53-229: Prior to the 
accumulation of 24,000 total flight cycles or within 12 years since 
new, whichever occurs first; or within 60 days after November 16, 
2011, whichever occurs later, do a detailed inspection of the 
fuselage bonded inner doubles of the longitudinal lap joints in 
Sections 16 and 17 at Stringer 31 left-hand and right-hand for 
disbonding and cracking, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-229, Revision 5, 
dated April 8, 1997. If no disbonding and no cracking are found, 
repeat the inspection thereafter at intervals not to exceed 7 years 
or 12,000 flight cycles, whichever occurs first.
    (1) If no cracking is found, and ``minor'' disbonding, as 
defined in Airbus Service Bulletin A300-53-229, Revision 5, dated 
April 8, 1997, is found: Repeat the inspection thereafter at 
intervals not to exceed 1 year for areas below stringer 22, and at 
intervals not to exceed 2 years for areas above and including 
stringer 22. Doing a repair in accordance with Airbus Service 
Bulletin A300-53-229, Revision 5, dated April 8, 1997, terminates 
the repetitive inspections required by this paragraph for that area.
    (2) If no cracking is found, and ``major'' disbonding, as 
defined in Airbus Service Bulletin A300-53-229, Revision 5, dated 
April 8, 1997, is found: Within 1,000 flight cycles after doing the 
inspection, repair, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-229, Revision 5, 
dated April 8, 1997.
    (3) If any cracking is found, repair prior to further flight, in 
accordance with Airbus Service Bulletin A300-53-229, Revision 5, 
dated April 8, 1997.

(k) Retained Fuselage Inner Doubler Inspections and Repair, With No 
Changes

    This paragraph restates the requirements of paragraph (o) of AD 
2011-17-05, with no changes. For airplanes on which any inspections 
of the fuselage bonded inner doublers of the longitudinal lap joints 
in Sections 16 and 17 at Stringer 31 left-hand and right-hand for 
disbonding and cracking have been done as of November 16, 2011, as 
specified in Airbus Service Bulletin A300-53-229; except airplanes 
on which a repair of that area has been done as specified in Airbus 
Service Bulletin A300-53-229: Within 7 years or 12,000 flight cycles 
after doing the inspection, whichever occurs first; or within 60 
days after November 16, 2011; whichever occurs later; do a detailed 
inspection of the fuselage bonded inner doubles of the longitudinal 
lap joints in Sections 16 and 17 at Stringer 31 left-hand and right-
hand for disbonding and cracking, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-229, 
Revision 5, dated April 8, 1997. If no disbonding and no corrosion 
are found, repeat the inspection thereafter at intervals not to 
exceed 7 years or 12,000 flight cycles, whichever occurs first.
    (1) If no cracking is found, and ``minor'' disbonding, as 
defined in Airbus Service Bulletin A300-53-229, Revision 5, dated 
April 8, 1997, is found: Repeat the inspection thereafter at 
intervals not to exceed 1 year for areas below stringer 22, and at 
intervals not to exceed 2 years for areas above and including 
stringer 22. Doing a repair, in accordance with Airbus Service 
Bulletin A300-53-229, Revision 5, dated April 8, 1997, terminates 
the repetitive inspections required by this paragraph for that area.
    (2) If no cracking is found, and ``major'' disbonding, as 
defined in Airbus Service Bulletin A300-53-229, Revision 5, dated 
April 8, 1997, is found: Within 1,000 flight cycles after doing the 
inspection, repair, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-229, Revision 5, 
dated April 8, 1997.
    (3) If any cracking is found, repair prior to further flight, in 
accordance with Airbus Service Bulletin A300-53-229, Revision 5, 
dated April 8, 1997.

(l) New Repetitive Inspections and Repair

    Within 180 days after the effective date of this AD, do rototest 
and ultrasonic inspections, as applicable, for cracking of all 
longitudinal lap joints and repairs between frames 18 and 80; and 
repair any cracking before further flight; 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). Repeat the 
applicable inspection, including post-repair inspections, thereafter 
at intervals approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. 
Accomplishing the initial inspection and applicable repairs required 
by this paragraph terminates the actions required by paragraphs (g) 
through (k) of this AD.

(m) 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. 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.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0265, dated December 9, 
2014, 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-2016-7425.
    (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 [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 June 23, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-15910 Filed 7-6-16; 8:45 am]
 BILLING CODE 4910-13-P



                                               44232

                                               Proposed Rules                                                                                                 Federal Register
                                                                                                                                                              Vol. 81, No. 130

                                                                                                                                                              Thursday, July 7, 2016



                                               This section of the FEDERAL REGISTER                       • Hand Delivery: U.S. Department of                 closing date and may amend this
                                               contains notices to the public of the proposed           Transportation, Docket Operations, M–                 proposed AD based on those comments.
                                               issuance of rules and regulations. The                   30, West Building Ground Floor, Room                    We will post all comments we
                                               purpose of these notices is to give interested           W12–140, 1200 New Jersey Avenue SE.,                  receive, without change, to http://
                                               persons an opportunity to participate in the             Washington, DC, between 9 a.m. and 5                  www.regulations.gov, including any
                                               rule making prior to the adoption of the final
                                               rules.
                                                                                                        p.m., Monday through Friday, except                   personal information you provide. We
                                                                                                        Federal holidays.                                     will also post a report summarizing each
                                                                                                          For service information identified in               substantive verbal contact we receive
                                               DEPARTMENT OF TRANSPORTATION                             this NPRM, contact Airbus SAS,                        about this proposed AD.
                                                                                                        Airworthiness Office—EAW, 1 Rond                      Discussion
                                               Federal Aviation Administration                          Point Maurice Bellonte, 31707 Blagnac
                                                                                                        Cedex, France; telephone +33 5 61 93 36                 On September 23, 2011, we issued AD
                                               14 CFR Part 39                                           96; fax +33 5 61 93 44 51; email                      2011–17–05, Amendment 39–16769 (76
                                                                                                        account.airworth-eas@airbus.com;                      FR 63177, October 12, 2011) (‘‘AD
                                               [Docket No. FAA–2016–7425; Directorate                                                                         2011–17–05’’). AD 2011–17–05 requires
                                               Identifier 2014–NM–244–AD]                               Internet http://www.airbus.com. You
                                                                                                        may view this referenced service                      actions intended to address an unsafe
                                               RIN 2120–AA64                                            information at the FAA, Transport                     condition on certain Airbus Model A300
                                                                                                        Airplane Directorate, 1601 Lind Avenue                B2–1C, A300 B2–203, A300 B2K–3C,
                                               Airworthiness Directives; Airbus                                                                               A300–B4–103, A300 B4–203, and A300
                                               Airplanes                                                SW., Renton, WA. For information on
                                                                                                        the availability of this material at the              B4–2C airplanes.
                                               AGENCY: Federal Aviation                                 FAA, call 425–227–1221.                                 Since we issued AD 2011–17–05, we
                                               Administration (FAA), DOT.                                                                                     have determined it is necessary to
                                                                                                        Examining the AD Docket                               require a revised inspection program for
                                               ACTION: Notice of proposed rulemaking
                                                                                                           You may examine the AD docket on                   the longitudinal lap joints and repairs
                                               (NPRM).
                                                                                                        the Internet at http://                               between FR 18 and FR 80 because
                                               SUMMARY:   We propose to supersede                       www.regulations.gov by searching for                  additional cracking was found in an
                                               Airworthiness Directive (AD) 2011–17–                    and locating Docket No. FAA–2016–                     expanded area.
                                               05, for certain Airbus Model A300 B2–                                                                            The European Aviation Safety Agency
                                                                                                        7425; or in person at the Docket
                                               1C, A300 B2–203, A300 B2K–3C, A300–                                                                            (EASA), which is the Technical Agent
                                                                                                        Management Facility between 9 a.m.
                                               B4–103, A300 B4–203, and A300 B4–2C                                                                            for the Member States of the European
                                                                                                        and 5 p.m., Monday through Friday,
                                               airplanes. AD 2011–17–05 currently                                                                             Union, has issued EASA Airworthiness
                                                                                                        except Federal holidays. The AD docket
                                               requires repetitive inspections in                                                                             Directive 2014–0265, dated December 9,
                                                                                                        contains this proposed AD, the
                                               sections 13 through 18 of the fuselage                                                                         2014 (referred to after this as the
                                                                                                        regulatory evaluation, any comments
                                               between rivets of the longitudinal lap                                                                         Mandatory Continuing Airworthiness
                                                                                                        received, and other information. The
                                               joints between frames (FR) 18 and 80 for                                                                       Information, or ‘‘the MCAI’’), to correct
                                                                                                        street address for the Docket Operations
                                               cracking, and repair or modification if                                                                        an unsafe condition for the specified
                                                                                                        office (telephone (800) 647–5527) is in
                                               necessary. Since we issued AD 2011–                                                                            products. The MCAI states:
                                                                                                        the ADDRESSES section. Comments will
                                               17–05, we have determined that a                         be available in the AD docket shortly                    Cracks were found on in-service aeroplanes
                                               revised inspection program is necessary.                 after receipt.                                        in sections 13 to 18 of the fuselage between
                                               This proposed AD would include a                                                                               rivets of longitudinal lap joints between
                                               revised repetitive inspection program of                 FOR FURTHER INFORMATION CONTACT:   Dan                frames (FR) 18 and FR80.
                                               all longitudinal lap joints and repairs                  Rodina, Aerospace Engineer,                              This condition, if not detected and
                                               between frames 18 and 80 to address                      International Branch, ANM–116,                        corrected, could affect the structural integrity
                                                                                                        Transport Airplane Directorate, FAA,                  of the aeroplane.
                                               this widespread fatigue damage (WFD).                                                                             To address this unsafe condition, Airbus
                                               We are proposing this AD to detect and                   1601 Lind Avenue SW., Renton, WA
                                                                                                        98057–3356; telephone 425–227–2125;                   developed an inspection programme for the
                                               correct fatigue cracking of the                                                                                longitudinal lap joints and repairs between
                                               longitudinal lap joints of the fuselage,                 fax 425- 227–1149.
                                                                                                                                                              FR18 and FR80, and EASA issued AD 2007–
                                               which could result in reduced structural                 SUPPLEMENTARY INFORMATION:                            0091 [which corresponds to FAA AD 2011–
                                               integrity of the airplane.                                                                                     17–05] to require the implementation of that
                                                                                                        Comments Invited                                      programme.
                                               DATES: We must receive comments on
                                               this proposed AD by August 22, 2016.                       We invite you to send any written                      Since EASA AD 2007–0091 was issued, [a]
                                                                                                                                                              new Widespread Fatigue Damage regulation
                                               ADDRESSES: You may send comments by                      relevant data, views, or arguments about              has been issued. This new regulation led to
                                               any of the following methods:                            this proposed AD. Send your comments                  the revision of the maintenance programme
                                                  • Federal eRulemaking Portal: Go to                   to an address listed under the                        for the longitudinal lap joints and repairs
                                                                                                        ADDRESSES section. Include ‘‘Docket No.
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                                               http://www.regulations.gov. Follow the                                                                         between FR18 and FR80.
                                               instructions for submitting comments.                    FAA–2016–7425; Directorate Identifier                    For the reasons described above, this
                                                  • Fax: (202) 493–2251.                                2014–NM–244–AD’’ at the beginning of                  [EASA] AD retains the requirements of EASA
                                                  • Mail: U.S. Department of                            your comments. We specifically invite                 AD 2007–0091, which is superseded, and
                                               Transportation, Docket Operations, M–                    comments on the overall regulatory,                   requires implementation of the revised
                                               30, West Building Ground Floor, Room                     economic, environmental, and energy                   inspection programme.
                                               W12–140, 1200 New Jersey Avenue SE.,                     aspects of this proposed AD. We will                    Required actions include repetitive
                                               Washington, DC 20590.                                    consider all comments received by the                 inspections of the bonded inner


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                                                                         Federal Register / Vol. 81, No. 130 / Thursday, July 7, 2016 / Proposed Rules                                           44233

                                               doublers of the longitudinal lap joints in               airplanes and all of these airplanes that             Design Authority, we have been notified
                                               sections 13 through 18 for disbonding or                 will be certificated in the future. For               of the unsafe condition described in the
                                               corrosion, and repairing any disbonding                  existing and future airplanes subject to              MCAI and service information
                                               and corrosion; a follow-on rototest or                   the WFD rule, the rule requires that                  referenced above. We are proposing this
                                               ultrasonic inspection to verify cracking,                DAHs establish a limit of validity (LOV)              AD because we evaluated all pertinent
                                               and repair of any cracking. The                          of the engineering data that support the              information and determined an unsafe
                                               repetitive inspection interval ranges                    structural maintenance program.                       condition exists and is likely to exist or
                                               from 3,000 flight cycles up to 8,000                     Operators affected by the WFD rule may                develop on other products of the same
                                               flight cycles, depending on airplane                     not fly an airplane beyond its LOV,                   type design.
                                               configuration. You may examine the                       unless an extended LOV is approved.
                                                                                                                                                              Differences Between This Proposed AD
                                               MCAI in the AD docket on the Internet                       The WFD rule (75 FR 69746,
                                                                                                                                                              and the MCAI or Service Information
                                               at http://www.regulations.gov by                         November 15, 2010) does not require
                                               searching for and locating it in Docket                  identifying and developing maintenance                  Unlike the procedures described in
                                               No. FAA–2016–7425.                                       actions if the DAHs can show that such                the service information, this proposed
                                                                                                        actions are not necessary to prevent                  AD would not permit further flight if
                                               Widespread Fatigue Damage                                                                                      cracks are detected. We have
                                                                                                        WFD before the airplane reaches the
                                                  Fatigue damage can occur locally, in                  LOV. Many LOVs, however, do depend                    determined that, because of the safety
                                               small areas or structural design details,                on accomplishment of future                           implications and consequences
                                               or globally, in widespread areas.                        maintenance actions. As stated in the                 associated with that cracking, any
                                               Multiple-site damage is widespread                       WFD rule, any maintenance actions                     cracked upper shell structure must be
                                               damage that occurs in a large structural                 necessary to reach the LOV will be                    repaired before further flight.
                                               element such as a single rivet line of a                 mandated by airworthiness directives                    The MCAI refers to Airbus Service
                                               lap splice joining two large skin panels.                through separate rulemaking actions.                  Bulletin A300–53–0211, Revision 08,
                                               Widespread damage can also occur in                         In the context of WFD, this action is              dated November 26, 2013, for
                                               multiple elements such as adjacent                       necessary to enable DAHs to propose                   compliance times and for the new
                                               frames or stringers. Multiple-site                       LOVs that allow operators the longest                 inspections. However, paragraph (l) of
                                               damage and multiple-element damage                       operational lives for their airplanes, and            this proposed AD would require
                                               cracks are typically too small initially to              still ensure that WFD will not occur.                 operators to do the initial inspections
                                               be reliably detected with normal                         This approach allows for an                           within 180 days after the effective date
                                               inspection methods. Without                              implementation strategy that provides                 of this AD, in a method approved by the
                                               intervention, these cracks will grow,                    flexibility to DAHs in determining the                Manager, International Branch, ANM–
                                               and eventually compromise the                            timing of service information                         116, Transport Airplane Directorate,
                                               structural integrity of the airplane. This               development (with FAA approval),                      FAA; or the European Aviation Safety
                                               condition is known as widespread                         while providing operators with certainty              Agency (EASA); or Airbus’s EASA
                                               fatigue damage. It is associated with                    regarding the LOV applicable to their                 Design Organization Approval (DOA);
                                               general degradation of large areas of                    airplanes.                                            and thereafter at intervals approved by
                                               structure with similar structural details                   We are issuing this AD to detect and               the Manager, International Branch,
                                               and stress levels. As an airplane ages,                  correct fatigue cracking of the                       ANM–116, Transport Airplane
                                               WFD will likely occur, and will                          longitudinal lap joints of the fuselage,              Directorate, FAA; or EASA; or Airbus’s
                                               certainly occur if the airplane is                       which could result in reduced structural              EASA DOA. We find that 180 days is an
                                               operated long enough without any                         integrity of the airplane.                            appropriate amount of time to
                                               intervention.                                                                                                  accomplish the initial inspections and
                                                  The FAA’s WFD final rule (75 FR                       FAA’s Determination and Requirements
                                                                                                                                                              address the unsafe condition.
                                               69746, November 15, 2010) became                         of This Proposed AD
                                                                                                                                                                These differences have been
                                               effective on January 14, 2011. The WFD                     This product has been approved by                   coordinated with the EASA and Airbus.
                                               rule requires certain actions to prevent                 the aviation authority of another
                                               structural failure due to WFD                            country, and is approved for operation                Costs of Compliance
                                               throughout the operational life of                       in the United States. Pursuant to our                    We estimate that this proposed AD
                                               certain existing transport category                      bilateral agreement with the State of                 affects 4 airplanes of U.S. registry.

                                                                                                                     ESTIMATED COSTS
                                                                                                                                                                               Cost per     Cost on U.S.
                                                                          Action                                                         Labor cost                            product       operators

                                               Retained actions from AD 2011–17–05 (5 airplanes) ..             3,735 work-hours × $85 per hour = $317,475 .............         $317,475     $1,587,375
                                               New proposed inspections (4 airplanes) ......................    140 work-hours × $85 per hour = $11,900 ..................         11,900         47,600



                                                 We have received no definitive data                    the FAA Administrator. ‘‘Subtitle VII:                air commerce by prescribing regulations
                                               that would enable us to provide cost                     Aviation Programs,’’ describes in more                for practices, methods, and procedures
                                               estimates for the on-condition actions                   detail the scope of the Agency’s
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                                                                                                                                                              the Administrator finds necessary for
                                               specified in this proposed AD.                           authority.                                            safety in air commerce. This regulation
                                                                                                          We are issuing this rulemaking under                is within the scope of that authority
                                               Authority for This Rulemaking                            the authority described in ‘‘Subtitle VII,            because it addresses an unsafe condition
                                                 Title 49 of the United States Code                     Part A, Subpart III, Section 44701:                   that is likely to exist or develop on
                                               specifies the FAA’s authority to issue                   General requirements.’’ Under that                    products identified in this rulemaking
                                               rules on aviation safety. Subtitle I,                    section, Congress charges the FAA with                action.
                                               section 106, describes the authority of                  promoting safe flight of civil aircraft in


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                                               44234                     Federal Register / Vol. 81, No. 130 / Thursday, July 7, 2016 / Proposed Rules

                                               Regulatory Findings                                      (d) Subject                                           paragraph (h)(1) or (h)(2) of this AD, repeat
                                                                                                          Air Transport Association (ATA) of                  the inspection required by paragraph (g) of
                                                 We determined that this proposed AD                                                                          this AD.
                                                                                                        America Code 53, Fuselage.
                                               would not have federalism implications                                                                            (1) For Sections 13 and 14 as specified in
                                               under Executive Order 13132. This                        (e) Reason                                            Airbus Service Bulletin A300–53–229,
                                               proposed AD would not have a                                This AD was prompted by an evaluation              Revision 5, dated April 8, 1997: Repeat the
                                               substantial direct effect on the States, on              done by the design approval holder                    inspection at intervals not to exceed 7 years
                                               the relationship between the national                    indicating that certain sections of the               or 12,000 flight cycles, whichever occurs
                                               Government and the States, or on the                     longitudinal lap joints are subject to                first.
                                                                                                        widespread fatigue damage. We are issuing                (2) For Sections 15 through 18 as specified
                                               distribution of power and
                                                                                                        this AD to detect and correct fatigue cracking        in Airbus Service Bulletin A300–53–229,
                                               responsibilities among the various                                                                             Revision 5, dated April 8, 1997: Repeat the
                                                                                                        of the longitudinal lap joints of the fuselage,
                                               levels of government.                                    which could result in reduced structural              inspection within 8.5 years or 12,000 flight
                                                 For the reasons discussed above, I                     integrity of the airplane.                            cycles, whichever occurs first.
                                               certify this proposed regulation:
                                                                                                        (f) Compliance                                        (i) Retained Fuselage Inner Doubler
                                                 1. Is not a ‘‘significant regulatory                                                                         Inspections and Repair
                                               action’’ under Executive Order 12866;                       Comply with this AD within the
                                                 2. Is not a ‘‘significant rule’’ under the             compliance times specified, unless already               This paragraph restates the requirements of
                                                                                                        done.                                                 paragraph (m) of AD 2011–17–05. For
                                               DOT Regulatory Policies and Procedures                                                                         airplanes on which any inspections of the
                                               (44 FR 11034, February 26, 1979);                        (g) Retained Fuselage Inner Doubler                   fuselage bonded inner doublers of the
                                                 3. Will not affect intrastate aviation in              Inspections and Repair, With Revised                  longitudinal lap joints in Sections 13 through
                                               Alaska; and                                              Formatting                                            18 (except Sections 16 and 17 at Stringer 31
                                                 4. Will not have a significant                            This paragraph restates the requirements of        left-hand and right-hand) for disbonding and
                                               economic impact, positive or negative,                   paragraph (l) of AD 2011–17–05, with revised          cracking have been done as of November 16,
                                               on a substantial number of small entities                formatting. For airplanes on which any                2011 (the effective date of AD 2011–17–05),
                                               under the criteria of the Regulatory                     inspections of the fuselage bonded inner              as specified in Airbus Service Bulletin A300–
                                                                                                        doublers of the longitudinal lap joints in            53–229; except for airplanes on which a
                                               Flexibility Act.
                                                                                                        Sections 13 through 18 (except Sections 16            repair of that area has been done as specified
                                               List of Subjects in 14 CFR Part 39                       and 17 at Stringer 31 left-hand and right-            in Airbus Service Bulletin A300–53–229:
                                                                                                        hand) for disbonding and cracking have not            Within 7 years or 12,000 flight cycles (for
                                                 Air transportation, Aircraft, Aviation                 been done as of November 16, 2011 (the                Sections 13 and 14), or within 8.5 years or
                                               safety, Incorporation by reference,                      effective date of AD 2011–17–05), as                  12,000 flight cycles (for Sections 15 and 18),
                                               Safety.                                                  specified by Airbus Service Bulletin A300–            after doing the inspection, whichever occurs
                                                                                                        53–229: Prior to the accumulation of 24,000           first; or within 60 days after November 16,
                                               The Proposed Amendment                                   total flight cycles or within 15 years since          2011, whichever occurs later, do a detailed
                                                 Accordingly, under the authority                       new, whichever occurs first; or within 60             inspection of the fuselage bonded inner
                                               delegated to me by the Administrator,                    days after November 16, 2011; whichever               doublers of the longitudinal lap joints in
                                               the FAA proposes to amend 14 CFR part                    occurs later; do a detailed inspection of the         Sections 13 through 18 (except Sections 16
                                                                                                        fuselage bonded inner doublers of the                 and 17 at Stringer 31 left-hand and right-
                                               39 as follows:                                           longitudinal lap joints in Sections 13 through        hand) for disbonding and cracking, in
                                                                                                        18 (except Sections 16 and 17 at Stringer 31          accordance with the Accomplishment
                                               PART 39—AIRWORTHINESS                                    left-hand and right-hand) for disbonding and          Instructions of Airbus Service Bulletin A300–
                                               DIRECTIVES                                               cracking, in accordance with the                      53–229, Revision 5, dated April 8, 1997. If no
                                                                                                        Accomplishment Instructions of Airbus                 disbonding and no cracking are found, repeat
                                               ■ 1. The authority citation for part 39                  Service Bulletin A300–53–229, Revision 5,             the inspection at the applicable time
                                               continues to read as follows:                            dated April 8, 1997. If no disbonding and no          specified in paragraph (h) of this AD.
                                                   Authority: 49 U.S.C. 106(g), 40113, 44701.           cracking are found, repeat the inspection                (1) If no cracking is found, and ‘‘minor’’
                                                                                                        thereafter at the applicable intervals specified      disbonding, as defined in Airbus Service
                                               § 39.13   [Amended]                                      in paragraph (h) of this AD.                          Bulletin A300–53–229, Revision 5, dated
                                               ■ 2. The FAA amends § 39.13 by                              (1) If no cracking is found, and ‘‘minor’’         April 8, 1997, is found: Repeat the inspection
                                                                                                        disbonding, as defined in Airbus Service              thereafter at intervals not to exceed 1 year for
                                               removing Airworthiness Directive (AD)
                                                                                                        Bulletin A300–53–229, Revision 5, dated               areas below stringer 22, and at intervals not
                                               2011–17–05, Amendment 39–16769 (76                       April 8, 1997, is found: Repeat the inspection        to exceed 2 years for areas above and
                                               FR 63177, October 12, 2011), and                         thereafter at intervals not to exceed 1 year for      including stringer 22.
                                               adding the following new AD:                             areas below stringer 22, and at intervals not            (2) If no cracking is found, and ‘‘major’’
                                               Airbus: Docket No. FAA–2016–7425;                        to exceed 2 years for areas above and                 disbonding, as defined in Airbus Service
                                                   Directorate Identifier 2014–NM–244–AD.               including stringer 22.                                Bulletin A300–53–229, Revision 5, dated
                                                                                                           (2) If no cracking is found, and ‘‘major’’         April 8, 1997, is found: Within 1,000 flight
                                               (a) Comments Due Date                                    disbonding, as defined in Airbus Service              cycles after doing the inspection, repair, in
                                                 We must receive comments by August 22,                 Bulletin A300–53–229, Revision 5, dated               accordance with the Accomplishment
                                               2016.                                                    April 8, 1997, is found: Within 1,000 flight          Instructions of Airbus Service Bulletin A300–
                                                                                                        cycles after doing the inspection, repair, in         53–229, Revision 5, dated April 8, 1997.
                                               (b) Affected ADs                                         accordance with the Accomplishment                       (3) If any cracking is found, repair prior to
                                                 This AD replaces AD 2011–17–05,                        Instructions of Airbus Service Bulletin A300–         further flight, in accordance with Airbus
                                               Amendment 39–16769 (76 FR 63177, October                 53–229, Revision 5, dated April 8, 1997.              Service Bulletin A300–53–229, Revision 5,
                                               12, 2011) (‘‘AD 2011–17–05’’).                              (3) If any cracking is found, repair prior to      dated April 8, 1997.
                                                                                                        further flight, in accordance with Airbus
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                                               (c) Applicability                                        Service Bulletin A300–53–229, Revision 5,             (j) Retained Fuselage Inner Doubler
                                                  This AD applies to Airbus Model A300 B2–              dated April 8, 1997.                                  Inspections and Repair, With No Changes
                                               1C, A300 B2–203, A300 B2K–3C, A300–B4–                                                                            This paragraph restates the requirements of
                                               103, A300 B4–203, and A300 B4–2C                         (h) Retained Repetitive Intervals for                 paragraph (n) of AD 2011–17–05, with no
                                               airplanes; certificated in any category; all             Inspections for Disbonding and Cracking               changes. For airplanes on which any
                                               manufacturer serial numbers, except those on               This paragraph restates the repetitive              inspections of the fuselage bonded inner
                                               which Airbus Modification 2611 has been                  intervals specified in table 1 of AD 2011–17–         doublers of the longitudinal lap joints in
                                               embodied in production.                                  05. At the applicable time specified in               Sections 16 and 17 at Stringer 31 left-hand



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                                                                         Federal Register / Vol. 81, No. 130 / Thursday, July 7, 2016 / Proposed Rules                                                44235

                                               and right-hand for disbonding and cracking               Bulletin A300–53–229, Revision 5, dated               accomplished using a method approved by
                                               have not been done as of November 16, 2011               April 8, 1997, is found: Repeat the inspection        the Manager, International Branch, ANM–
                                               (the effective date of AD 2011–17–05), as                thereafter at intervals not to exceed 1 year for      116, Transport Airplane Directorate, FAA; or
                                               specified in Airbus Service Bulletin A300–               areas below stringer 22, and at intervals not         the EASA; or Airbus’s EASA DOA. If
                                               53–229: Prior to the accumulation of 24,000              to exceed 2 years for areas above and                 approved by the DOA, the approval must
                                               total flight cycles or within 12 years since             including stringer 22. Doing a repair, in             include the DOA-authorized signature.
                                               new, whichever occurs first; or within 60                accordance with Airbus Service Bulletin
                                               days after November 16, 2011, whichever                  A300–53–229, Revision 5, dated April 8,               (n) Related Information
                                               occurs later, do a detailed inspection of the            1997, terminates the repetitive inspections              (1) Refer to Mandatory Continuing
                                               fuselage bonded inner doubles of the                     required by this paragraph for that area.             Airworthiness Information (MCAI) EASA
                                               longitudinal lap joints in Sections 16 and 17              (2) If no cracking is found, and ‘‘major’’          Airworthiness Directive 2014–0265, dated
                                               at Stringer 31 left-hand and right-hand for              disbonding, as defined in Airbus Service              December 9, 2014, for related information.
                                               disbonding and cracking, in accordance with              Bulletin A300–53–229, Revision 5, dated               This MCAI may be found in the AD docket
                                               the Accomplishment Instructions of Airbus                April 8, 1997, is found: Within 1,000 flight          on the Internet at http://www.regulations.gov
                                               Service Bulletin A300–53–229, Revision 5,                cycles after doing the inspection, repair, in         by searching for and locating Docket No.
                                               dated April 8, 1997. If no disbonding and no             accordance with the Accomplishment                    FAA–2016–7425.
                                               cracking are found, repeat the inspection                Instructions of Airbus Service Bulletin A300–            (2) For service information identified in
                                               thereafter at intervals not to exceed 7 years            53–229, Revision 5, dated April 8, 1997.              this AD, contact Airbus SAS, Airworthiness
                                               or 12,000 flight cycles, whichever occurs                  (3) If any cracking is found, repair prior to       Office—EAW, 1 Rond Point Maurice
                                               first.                                                   further flight, in accordance with Airbus             Bellonte, 31707 Blagnac Cedex, France;
                                                  (1) If no cracking is found, and ‘‘minor’’            Service Bulletin A300–53–229, Revision 5,             telephone +33 5 61 93 36 96; fax +33 5 61
                                               disbonding, as defined in Airbus Service                 dated April 8, 1997.                                  93 44 51; email account.airworth-eas@
                                               Bulletin A300–53–229, Revision 5, dated                                                                        airbus.com; Internet http://www.airbus.com.
                                               April 8, 1997, is found: Repeat the inspection           (l) New Repetitive Inspections and Repair             You may view this service information at the
                                               thereafter at intervals not to exceed 1 year for            Within 180 days after the effective date of        FAA, Transport Airplane Directorate, 1601
                                               areas below stringer 22, and at intervals not            this AD, do rototest and ultrasonic                   Lind Avenue SW., Renton, WA. For
                                               to exceed 2 years for areas above and                    inspections, as applicable, for cracking of all       information on the availability of this
                                               including stringer 22. Doing a repair in                 longitudinal lap joints and repairs between           material at the FAA, call 425–227–1221.
                                               accordance with Airbus Service Bulletin                  frames 18 and 80; and repair any cracking
                                                                                                                                                                Issued in Renton, Washington, on June 23,
                                               A300–53–229, Revision 5, dated April 8,                  before further flight; using a method
                                                                                                                                                              2016.
                                               1997, terminates the repetitive inspections              approved by the Manager, International
                                               required by this paragraph for that area.                Branch, ANM–116, Transport Airplane                   Dorr M. Anderson,
                                                  (2) If no cracking is found, and ‘‘major’’            Directorate, FAA; or the European Aviation            Acting Manager, Transport Airplane
                                               disbonding, as defined in Airbus Service                 Safety Agency (EASA); or Airbus’s EASA                Directorate, Aircraft Certification Service.
                                               Bulletin A300–53–229, Revision 5, dated                  Design Organization Approval (DOA). Repeat            [FR Doc. 2016–15910 Filed 7–6–16; 8:45 am]
                                               April 8, 1997, is found: Within 1,000 flight             the applicable inspection, including post-            BILLING CODE 4910–13–P
                                               cycles after doing the inspection, repair, in            repair inspections, thereafter at intervals
                                               accordance with the Accomplishment                       approved by the Manager, International
                                               Instructions of Airbus Service Bulletin A300–            Branch, ANM–116, Transport Airplane
                                                                                                                                                              DEPARTMENT OF TRANSPORTATION
                                               53–229, Revision 5, dated April 8, 1997.                 Directorate, FAA; or EASA; or Airbus’s EASA
                                                  (3) If any cracking is found, repair prior to         DOA. Accomplishing the initial inspection
                                                                                                                                                              Federal Aviation Administration
                                               further flight, in accordance with Airbus                and applicable repairs required by this
                                               Service Bulletin A300–53–229, Revision 5,                paragraph terminates the actions required by
                                               dated April 8, 1997.                                     paragraphs (g) through (k) of this AD.                14 CFR Part 39
                                               (k) Retained Fuselage Inner Doubler                      (m) Other FAA AD Provisions                           [Docket No. FAA–2016–7424; Directorate
                                               Inspections and Repair, With No Changes                                                                        Identifier 2015–NM–173–AD]
                                                                                                           The following provisions also apply to this
                                                 This paragraph restates the requirements of            AD:                                                   RIN 2120–AA64
                                               paragraph (o) of AD 2011–17–05, with no                     (1) Alternative Methods of Compliance
                                               changes. For airplanes on which any                      (AMOCs): The Manager, International                   Airworthiness Directives; Airbus
                                               inspections of the fuselage bonded inner                 Branch, ANM–116, Transport Airplane                   Airplanes
                                               doublers of the longitudinal lap joints in               Directorate, FAA, has the authority to
                                               Sections 16 and 17 at Stringer 31 left-hand              approve AMOCs for this AD, if requested               AGENCY: Federal Aviation
                                               and right-hand for disbonding and cracking               using the procedures found in 14 CFR 39.19.           Administration (FAA), DOT.
                                               have been done as of November 16, 2011, as               In accordance with 14 CFR 39.19, send your            ACTION: Notice of proposed rulemaking
                                               specified in Airbus Service Bulletin A300–               request to your principal inspector or local          (NPRM).
                                               53–229; except airplanes on which a repair               Flight Standards District Office, as
                                               of that area has been done as specified in               appropriate. If sending information directly          SUMMARY:    We propose to adopt a new
                                               Airbus Service Bulletin A300–53–229:                     to the International Branch, send it to ATTN:         airworthiness directive (AD) for all
                                               Within 7 years or 12,000 flight cycles after             Dan Rodina, Aerospace Engineer,
                                                                                                                                                              Airbus Model A330–200, –200
                                               doing the inspection, whichever occurs first;            International Branch, ANM–116, Transport
                                               or within 60 days after November 16, 2011;               Airplane Directorate, FAA, 1601 Lind                  Freighter, and –300 series airplanes; and
                                               whichever occurs later; do a detailed                    Avenue SW., Renton, WA 98057–3356;                    Model A340–200, –300, –500, and –600
                                               inspection of the fuselage bonded inner                  telephone 425–227–2125; fax 425–227–1149.             series airplanes. This proposed AD was
                                               doubles of the longitudinal lap joints in                Information may be emailed to: 9-ANM-116-             prompted by a determination that, due
                                               Sections 16 and 17 at Stringer 31 left-hand              AMOC-REQUESTS@faa.gov. Before using                   to significant differences among all
                                               and right-hand for disbonding and cracking,              any approved AMOC, notify your appropriate            airspeed sources, the flight controls will
                                               in accordance with the Accomplishment                    principal inspector, or lacking a principal           revert to alternate law, the autopilot
Lhorne on DSK30JT082PROD with PROPOSALS




                                               Instructions of Airbus Service Bulletin A300–            inspector, the manager of the local flight            (AP) and the auto-thrust (A/THR) will
                                               53–229, Revision 5, dated April 8, 1997. If no           standards district office/certificate holding
                                                                                                                                                              automatically disconnect, and the flight
                                               disbonding and no corrosion are found,                   district office. The AMOC approval letter
                                               repeat the inspection thereafter at intervals            must specifically reference this AD.                  director (FD) bars will be automatically
                                               not to exceed 7 years or 12,000 flight cycles,              (2) Contacting the Manufacturer: As of the         removed. Then, if two airspeed sources
                                               whichever occurs first.                                  effective date of this AD, for any requirement        become similar while still erroneous,
                                                 (1) If no cracking is found, and ‘‘minor’’             in this AD to obtain corrective actions from          the flight guidance computers will
                                               disbonding, as defined in Airbus Service                 a manufacturer, the action must be                    display the FD bars again, and enable


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Document Created: 2018-02-08 07:54:27
Document Modified: 2018-02-08 07:54:27
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionProposed Rules
ActionNotice of proposed rulemaking (NPRM).
DatesWe must receive comments on this proposed AD by August 22, 2016.
ContactDan 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.
FR Citation81 FR 44232 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

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