[Federal Register Volume 79, Number 104 (Friday, May 30, 2014)]
[Proposed Rules]
[Pages 31057-31061]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-12613]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0291; Directorate Identifier 2013-NM-137-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2004-03-
19, which applies to certain Airbus Model A320-111, -211, and -231
series airplanes. AD 2004-03-19 requires repetitive inspections for
cracking in the transition and pick-up angles in the lower part of the
center fuselage area, and corrective action if necessary. AD 2004-03-19
also provides for an optional terminating modification for the
repetitive inspection requirements. Since we issued AD 2004-03-19, we
have determined that the modification must be accomplished in order to
address the unsafe condition. This proposed AD would also require that
modification by installing washers between the transition pick-up angle
and the pin nuts, and doing related investigative and corrective
actions if necessary. This proposed AD would also add airplanes to the
applicability. We are proposing this AD to prevent fatigue cracking in
the transition and pick-up angles of the lower part of the center
fuselage, which could result in reduced structural integrity of the
wing-fuselage support and fuselage pressure vessel.
DATES: We must receive comments on this proposed AD by July 14, 2014.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus, Airworthiness Office--EIAS, 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-2014-
0291; 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
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: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
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-2014-0291;
Directorate Identifier 2013-NM-137-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
[[Page 31058]]
substantive verbal contact we receive about this proposed AD.
Discussion
On January 30, 2004, we issued AD 2004-03-19, Amendment 39-13463
(69 FR 5922, February 9, 2004). AD 2004-03-19 requires actions intended
to address an unsafe condition on certain Airbus Model A320-111, -211,
and -231 series airplanes. (AD 2004-03-19 superseded AD 98-12-18,
Amendment 39-10573 (63 FR 31345, June 9, 1998)).
Since we issued AD 2004-03-19, Amendment 39-13463 (69 FR 5922,
February 9, 2004), we have determined that the optional modification
specified in AD 2004-03-19 must be accomplished in order to address the
identified unsafe condition.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2013-0137, dated July 9, 2013 (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:
During the A320 fatigue test campaign, it has been determined
that fatigue damage could appear on the transition and pick-up angle
between Frame (FR) 35 and FR36.
This condition, if not detected and corrected, could affect the
structural integrity of the aeroplane.
To address this potential unsafe condition, DGAC [Direction
G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 2002-
183 [related to FAA AD 2004-03-19, Amendment 39-13463 (69 FR 5922,
February 9, 2004)], to require repetitive inspections of the center
fuselage pick-up angle between FR35 and FR36, below stringer 30,
left hand (LH) and right hand (RH) sides, and, depending on
findings, accomplishment of applicable corrective action(s).
Since that [DGAC] AD [2002-183] was issued, a modification was
developed, which has been published through Airbus Service Bulletin
(SB) A320-53-1027 for in-service application, introducing additional
washers below the riveting, which constitutes terminating action for
the repetitive inspections.
For the reasons described above, this [EASA] AD retains the
requirements of DGAC France AD 2002-183, which is superseded, and
requires modification of the transition and pick-up angle between
FR35 and FR36.
You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0291.
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.
Change to Applicability
We have added Airbus Model A320-212 airplanes to the applicability,
(paragraph (c) of this NPRM) because these airplanes are subject to the
same unsafe condition identified on Airbus Model A320-111, A320-211,
and A320-231 airplanes. We have also revised the applicability language
used in AD 2004-03-19, Amendment 39-13463 (69 FR 5922, February 9,
2004). This proposed AD applies to Airbus Model A320-111, -211, -212,
and -231 airplanes, all manufacturer serial numbers. We have added new
paragraph (n) in this proposed AD to specify that accomplishing Airbus
Modification 21202 in production terminates the requirements of this
AD.
Clarification of Modification Actions
The optional modification specified in paragraph (e) of AD 2004-03-
19, Amendment 39-13463 (69 FR 5922, February 9, 2004), is proposed to
be required in paragraph (m) of this NPRM. The modification includes
rotating probe inspections for cracking of certain fastener holes and,
if any cracking is found, replacement or repair of certain parts. We
have included these inspections, as well as the replacement of
transition angles if cracking is found in the transition angles and
repair if cracking is found in the pick-up angles, in the description
of the modification in paragraph (m) of this NPRM.
Repair Approvals
In many FAA transport ADs, when the service information specifies
to contact the manufacturer for further instructions if certain
discrepancies are found, we typically include in the AD a requirement
to accomplish the action using a method approved by either the FAA or
the State of Design Authority (or its delegated agent).
We have recently been notified that certain laws in other countries
do not allow such delegation of authority, but some countries do
recognize design approval organizations. In addition, we have become
aware that some U.S. operators have used repair instructions that were
previously approved by a State of Design Authority or a Design Approval
Holder (DAH) as a method of compliance with this provision in FAA ADs.
Frequently, in these cases, the previously approved repair instructions
come from the airplane structural repair manual or the DAH repair
approval statements that were not specifically developed to address the
unsafe condition corrected by the AD. Using repair instructions that
were not specifically approved for a particular AD creates the
potential for doing repairs that were not developed to address the
unsafe condition identified by the MCAI AD, the FAA AD, or the
applicable service information, which could result in the unsafe
condition not being fully corrected.
To prevent the use of repairs that were not specifically developed
to correct the unsafe condition, certain requirements of this proposed
AD would require that the repair approval specifically refer to the FAA
AD. This change is intended to clarify the method of compliance and to
provide operators with better visibility of repairs that are
specifically developed and approved to correct the unsafe condition. In
addition, we use the phrase ``its delegated agent, or the DAH with
State of Design Authority design organization approval, as applicable''
in this proposed AD to refer to a DAH authorized to approve certain
required repairs for this proposed AD.
Costs of Compliance
We estimate that this proposed AD affects 482 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
[[Page 31059]]
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Inspection [retained action from 9 work-hours x $85 $0 $765 per inspection $18,360 per
AD 2004-03-19, Amendment 39- per hour = $765 cycle. inspection cycle
13463 (69 FR 5922, February 9, per inspection (24 airplanes).
2004)]. cycle.
Inspection for Model A320-212 9 work-hours x $85 0 $765 per inspection $32,130 per
airplanes [new proposed action]. per hour = $765 cycle. inspection cycle
per inspection (42 airplanes).
cycle.
Terminating modification [new 28 work-hours x $85 1,837 $4,217............. $2,032,594.
proposed action]. per hour = $2,380.
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
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. Amend Sec. 39.13 by removing airworthiness directive (AD) 2004-03-
19, Amendment 39-13463 (69 FR 5922, February 9, 2004), and adding the
following new AD:
Airbus: Docket No. FAA-2014-0291; Directorate Identifier 2013-NM-
137-AD.
(a) Comments Due Date
We must receive comments by July 14, 2014.
(b) Affected ADs
This AD supersedes AD 2004-03-19, Amendment 39-13463 (69 FR
5922, February 9, 2004).
(c) Applicability
This AD applies to Airbus Model A320-111, -211, -212, and -231
airplanes, certificated in any category, all manufacturer serial
numbers.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by the determination that the modification
must be accomplished in order to address the unsafe condition. We
are issuing this AD to prevent fatigue cracking in the transition
and pick-up angles of the lower part of the center fuselage, which
could result in reduced structural integrity of the wing-fuselage
support and fuselage pressure vessel.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Detailed and Rotating Probe Inspections
This paragraph restates the requirements of paragraph (b) of AD
2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004). For
Model A320-111, -211, and -231 airplanes on which the modification
specified in AD 98-12-18, Amendment 39-10573 (63 FR 31345, June 9,
1998), has not been done: Do the applicable inspections specified in
paragraphs (g)(1) and (g)(2) of this AD, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-53-1028,
Revision 01, dated February 12, 2002.
(1) For airplanes on which the inspections required by AD 98-12-
18, Amendment 39-10573 (63 FR 31345, June 9, 1998), have been done:
Within 12,000 flight cycles after accomplishment of the last
inspection required by AD 98-12-18, do a detailed inspection of the
transition angle and a rotating probe inspection of the pick-up
angle in the lower part of the center fuselage area for cracking.
(2) For airplanes on which the inspections required by AD 98-12-
18, Amendment 39-10573 (63 FR 31345, June 9, 1998), have not been
done: At the later of the times specified in paragraph (g)(2)(i) or
(g)(2)(ii) of this AD, do a detailed inspection of the transition
angle and a rotating probe inspection of the pick-up angle in the
lower part of the center fuselage area for cracking.
(i) Before the accumulation of 10,400 total flight cycles, or
24,600 total flight hours, whichever is first.
(ii) Before the accumulation of 16,000 total flight cycles, or
within 3,500 flight cycles after March 15, 2004 (the effective date
of AD 2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004),
whichever is first.
(h) Retained Repetitive Inspections
This paragraph restates the requirements of paragraph (c) of AD
2004-03-19, Amendment 39-13463 (69 FR 5922, February 9, 2004). For
Model A320-111, -211, and -231 airplanes: Repeat the detailed and
rotating probe inspections specified in paragraphs (g)(1) and (g)(2)
of this AD at intervals not to exceed 10,400 flight cycles or 24,600
flight hours, whichever is first, until the modification specified
in paragraph (m) of this AD has been done.
(i) Retained Corrective Action for Paragraphs (g) and (h) of This AD
This paragraph restates the requirements of paragraph (d) of AD
2004-03-19,
[[Page 31060]]
Amendment 39-13463 (69 FR 5922, February 9, 2004). For Model A320-
111, -211, and -231 airplanes: If any cracking is found during any
inspection required by paragraph (g) or (h) of this AD, prior to
further flight, either repair the cracking per the Accomplishment
Instructions of Airbus Service Bulletin A320-53-1028, Revision 01,
dated February 12, 2002; or do the modification specified in
paragraph (m) of this AD. Where Airbus Service Bulletin A320-53-
1028, Revision 01, dated February 12, 2002, specifies to contact the
manufacturer for repair instructions, prior to further flight,
repair the cracking in accordance with a method approved by the
Manager, International Branch, ANM-116 Transport Airplane
Directorate, FAA; or European Aviation Safety Agency (EASA) or the
Direction G[eacute]n[eacute]rale de l'Aviation Civile (or its
delegated agent). If the cracking is repaired, repeat the
inspections as required by paragraph (h) of this AD.
(j) New Detailed and Rotating Probe Inspections for Model A320-212
Airplanes
For Model A320-212 airplanes on which the modification specified
in Airbus Service Bulletin A320-53-1027, has not been done as of the
effective date of this AD: Do the applicable inspections specified
in paragraph (j)(1) or (j)(2) of this AD, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-53-1028,
Revision 01, dated February 12, 2002.
(1) For airplanes on which the inspections specified in Airbus
Service Bulletin A320-53-1028 have been done as of the effective
date of this AD: At the later of the times specified in paragraph
(j)(1)(i) or (j)(1)(ii) of this AD, do a detailed inspection of the
transition angle and a rotating probe inspection of the pick-up
angle in the lower part of the center fuselage area for cracking.
(i) Within 10,400 flight cycles or 24,600 flight hours,
whichever occurs first after accomplishing the most recent
inspection specified in Airbus Service Bulletin A320-53-1028.
(ii) Within 90 days after the effective date of this AD.
(2) For airplanes on which the inspections specified in Airbus
Service Bulletin A320-53-1028 have not been done as of the effective
date of this AD: At the later of the times specified in paragraphs
(j)(2)(i) and (j)(2)(ii) of this AD, do a detailed inspection of the
transition angle and a rotating probe inspection of the pick-up
angle in the lower part of the center fuselage area for cracking.
(i) Before the accumulation of 10,400 total flight cycles, or
24,600 total flight hours, whichever occurs first.
(ii) Within 90 days after the effective date of this AD.
(k) New Repetitive Inspections for Model A320-212 Airplanes
For Model A320-212 airplanes: Repeat the detailed and rotating
probe inspections specified in paragraphs (j)(1) and (j)(2) of this
AD at intervals not to exceed 10,400 flight cycles or 24,600 flight
hours, whichever occurs first, until the modification specified in
paragraph (m) of this AD has been done.
(l) New Corrective Action for Model A320-212 Airplanes
For Model A320-212 airplanes: If any cracking is found during
any inspection required by paragraph (j) or (k) of this AD, before
further flight, do the actions specified in either paragraph (l)(1)
or (l)(2) of this AD.
(1) Repair the crack in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-53-1028, Revision 01,
dated February 12, 2002, except where Airbus Service Bulletin A320-
53-1028, Revision 01, dated February 12, 2002, specifies to contact
the manufacturer, before further flight, repair using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or European Aviation Safety Agency
(EASA), or its delegated agent, or the design approval holder (DAH)
with EASA's design organization approval, as applicable. For a
repair method to be approved, the repair approval must specifically
refer to this AD. After the cracking is repaired, repeat the
inspections required by paragraph (k) of this AD.
(2) Do the modification specified in paragraph (m) of this AD.
(m) New Terminating Modification for All Airplanes
For all airplanes: Before the accumulation of 40,000 flight
cycles since first flight, or within 1,500 flight cycles after the
effective date of this AD, whichever occurs later, but not exceeding
48,000 flight cycles since first flight, modify by doing rotating
probe inspections for cracking of certain fastener holes, replacing
transition angles if any cracking is found in the transition angles,
repairing if any pick-up angles cracking is found, and installing
washers between the transition pick-up angle and the pin nuts; in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-53-1027, Revision 03, dated February 12, 2002, except
where Airbus Service Bulletin A320-53-1027, Revision 03, dated
February 12, 2001, specifies to contact Airbus, before further
flight, repair using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA, or
its delegated agent; or the DAH with EASA's design organization
approval, as applicable. For a repair method to be approved, the
repair approval must specifically refer to this AD. Accomplishment
of this modification terminates the repetitive inspections required
by paragraphs (h) and (k) of this AD.
(n) Terminating Modification
For airplanes on which Airbus Modification 21202 has been
embodied in production: No actions are required by this AD.
(o) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraph (j) of this AD, if those actions were performed before the
effective date of this AD using Airbus Service Bulletin A320-53-
1028, dated March 1, 1994.
(2) This paragraph provides credit for the action specified in
paragraph (m) of this AD, if that action was performed before the
effective date of this AD using Airbus Service Bulletin A320-53-
1027, dated March 1, 1994; Revision 1, dated September 5, 1994; or
Revision 2, dated June 8, 1995.
(p) 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: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; 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. AMOCs
approved previously in accordance with AD 2004-03-19, Amendment 39-
13463 (69 FR 5922, February 9, 2004), are approved as AMOCs for the
corresponding provisions of this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer, use these actions if they
are FAA approved. Corrective actions are considered FAA-approved if
they were approved by the State of Design Authority (or its
delegated agent, or the DAH with a State of Design Authority's
design organization approval, as applicable). You are required to
ensure the product is airworthy before it is returned to service.
(q) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2013-0137, dated July 9, 2013,
for related information. This MCAI may be found in the AD docket on
the Internet at http://www.regulations.gov by searching for and
locating Docket No. FAA-2014-0291.
(2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 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.
[[Page 31061]]
Issued in Renton, Washington, on May 15, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-12613 Filed 5-29-14; 8:45 am]
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