
[Federal Register Volume 81, Number 243 (Monday, December 19, 2016)]
[Rules and Regulations]
[Pages 91695-91698]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-29511]



[[Page 91695]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-7425; Directorate Identifier 2014-NM-244-AD; 
Amendment 39-18741; AD 2016-25-15]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are superseding 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 required 
repetitive inspections in sections 13 through 18 of the fuselage 
between rivets of the longitudinal lap joints between frames (FRs) 18 
and 80 for cracking, and repair or modification if necessary. This new 
AD requires a revised repetitive inspection program of all longitudinal 
lap joints and repairs between FRs 18 and 80 to address widespread 
fatigue damage (WFD). 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 WFD; therefore, a revised 
inspection program is necessary. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective January 23, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 16, 
2011 (76 FR 63177, October 12, 2011).

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet 
http://www.airbus.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7425.

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 AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2011-17-05, Amendment 39-16769 (76 FR 63177, 
October 12, 2011) (``AD 2011-17-05''). AD 2011-17-05 applied to certain 
Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300-B4-103, A300 
B4-203, and A300 B4-2C airplanes. The NPRM published in the Federal 
Register on July 7, 2016 (81 FR 44232). The NPRM was prompted by an 
evaluation done by the design approval holder indicating that certain 
sections of the longitudinal lap joints are subject to WFD. The NPRM 
proposed to continue to require repetitive inspections in sections 13 
through 18 of the fuselage between rivets of the longitudinal lap 
joints between FRs 18 and 80 for cracking, and repair or modification 
if necessary. The NPRM also proposed to require a revised repetitive 
inspection program of all longitudinal lap joints and repairs between 
FRs 18 and 80 to address this WFD. 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.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
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 
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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed, except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Costs of Compliance

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

[[Page 91696]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                    Action                                 Labor cost                 product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2011-17-05...........  3,735 work-hours x $85 per hour         $317,475      $1,269,900
                                                 = $317,475.
New inspections...............................  140 work-hours x $85 per hour =          $11,900         $47,600
                                                 $11,900.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that enables us to provide cost 
estimates for the on-condition actions specified in this 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 AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2011-17-05, Amendment 39-16769 (76 FR 63177, October 12, 2011), and 
adding the following new AD:

2016-25-15 Airbus: Amendment 39-18741; Docket No. FAA-2016-7425; 
Directorate Identifier 2014-NM-244-AD.

(a) Effective Date

    This AD is effective January 23, 2017.

(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, With No Changes

    This paragraph restates the repetitive intervals specified in 
table 1 of AD 2011-17-05, with no changes. 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.

[[Page 91697]]

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

    This paragraph restates the requirements of paragraph (m) 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 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 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 
doublers 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 doublers 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: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(n) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA AD 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.

[[Page 91698]]

(o) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
November 16, 2011 (76 FR 63177, October 12, 2011).
    (i) Airbus Service Bulletin A300-53-229, Revision 5, dated April 
8, 1997, including Appendix A300SB/53-229, dated April 10, 1989. 
Only pages 1, 2, 5, 11, and 12 of Airbus Service Bulletin A300-53-
229, Revision 5, dated April 8, 1997, show revision level 5 and 
issue date April 8, 1997; pages 3, 4-10, and 13-17 show revision 
level 4 and issue date March 30, 1994; and pages 1-17 of Appendix 
A300SB/53-229 show issue date April 10, 1989.
    (ii) Reserved.
    (4) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet http://www.airbus.com.
    (5) 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.
    (6) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on December 1, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-29511 Filed 12-16-16; 8:45 am]
 BILLING CODE 4910-13-P


