80 FR 74058 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 228 (November 27, 2015)

We propose to supersede Airworthiness Directive (AD) 2004-19- 11 for certain Airbus Model 320 series airplanes. AD 2004-19-11 currently requires modification of the inner rear spar web of the wing, cold expansion of the attachment holes of the forward pintle fitting and the actuating cylinder anchorage of the main landing gear (MLG), repetitive ultrasonic inspections for cracking of the rear spar of the wing, and corrective action if necessary. AD 2004-19-11 also provides optional terminating action for the repetitive inspections. Since we issued AD 2004-19-11, we have determined that the terminating action is necessary to address the unsafe condition. This proposed AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This proposed AD would retain the requirements of AD 2004-19-11 and would require the previously optional terminating action. We are proposing this AD to prevent fatigue cracking of the inner rear spar, which may lead to reduced structural integrity of the wing and the MLG.

[Federal Register Volume 80, Number 228 (Friday, November 27, 2015)]
[Proposed Rules]
[Pages 74058-74061]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-30006]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-5811; Directorate Identifier 2014-NM-158-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) 2004-19-
11 for certain Airbus Model 320 series airplanes. AD 2004-19-11 
currently requires modification of the inner rear spar web of the wing, 
cold expansion of the attachment holes of the forward pintle fitting 
and the actuating cylinder anchorage of the main landing gear (MLG), 
repetitive ultrasonic inspections for cracking of the rear spar of the 
wing, and corrective action if necessary. AD 2004-19-11 also provides 
optional terminating action for the repetitive inspections. Since we 
issued AD 2004-19-11, we have determined that the terminating action is 
necessary to address the unsafe condition. This proposed AD is intended 
to complete certain mandated programs intended to support the airplane 
reaching its limit of validity (LOV) of the engineering data that 
support the established structural maintenance program. This proposed 
AD would retain the requirements of AD 2004-19-11 and would require the 
previously optional terminating action. We are proposing this AD to 
prevent fatigue cracking of the inner rear spar, which may lead to 
reduced structural integrity of the wing and the MLG.

DATES: We must receive comments on this proposed AD by January 11, 
2016.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus, 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-2015-
5811; 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 ADDRESSESsection. 
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-2015-5811; 
Directorate Identifier 2014-NM-158-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 21, 2004, we issued AD 2004-19-11, Amendment 39-13805 
(69 FR 58828, October 1, 2004). AD 2004-19-11 requires actions intended 
to address an unsafe condition on certain Airbus Model 320 series 
airplanes. AD 2004-19-11 superseded AD 2000-10-15, Amendment 39-17739 
(65 FR 34069, May 26, 2000).
    Since we issued AD 2004-19-11, Amendment 39-13805 (69 FR 58828, 
October 1, 2004), we have determined that the modification of the inner 
rear spar that is an optional terminating action of AD 2004-19-11 must 
be accomplished in order to address the identified unsafe condition.
    As described in FAA Advisory Circular 120-104 (http://www.faa.gov/documentLibrary/media/Advisory_Circular/120-104.pdf), several programs 
have been developed to support initiatives that will ensure the 
continued airworthiness of aging airplane structure. The last element 
of those initiatives is the requirement to establish a limit of 
validity (LOV) of the engineering data that support the structural 
maintenance program under 14 CFR 26.21. This proposed AD is the result 
of an assessment of the previously established programs by the design 
approval holder (DAH). The actions specified in this proposed AD are 
necessary to complete certain programs to ensure the continued 
airworthiness of aging airplane structure and to support an airplane 
reaching its LOV.
    The European Aviation Safety Agency, which is the Technical Agent 
for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0169, corrected July 22, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on certain Airbus Model 
A320 series airplanes. The MCAI states:

    During centre fuselage certification full scale fatigue test, 
cracks were found on the

[[Page 74059]]

inner rear spar at holes position 52 on the right hand wing due to 
fatigue aspects.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    To prevent such cracks, Airbus developed modifications, which 
were introduced in production and in service through several Airbus 
Service Bulletins (SB). DGAC France issued * * * [an earlier AD], 
which was subsequently superseded by [DGAC] AD 2001-249 [which 
corresponds with FAA AD 2004-19-11, Amendment 39-13805 (69 FR 58828, 
October 1, 2004)], to require modification of the rear spar on some 
aeroplanes, post-modification repetitive inspections and, depending 
on findings, accomplishment of a repair. DGAC France AD 2001-249 
also specified that modification in accordance with Airbus SB A320-
57-1089 (in-service equivalent to Airbus mod 24591) constituted 
(optional) terminating action for the repetitive inspections.
    Since that [DGAC] AD [2001-249] was issued, in the framework of 
the A320 Extended Service Goal (ESG), it has been determined that 
Airbus mod 24591 is necessary to allow aeroplanes to operate up to 
the new ESG limit.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD 2001-249, which is superseded, and 
requires modification of all pre-mod 24591 aeroplanes.

    The modification includes modifying all specified fastener holes in 
the inner rear spar of the wing. You may examine the MCAI in the AD 
docket on the Internet at http://www.regulations.gov by searching for 
and locating Docket No. FAA-2015-5811.

Related Service Information Under 1 CFR part 51

    Airbus has issued the following service information.
     Airbus Service Bulletin A320-57-1004, Revision 02, dated 
June 14, 1993. This service information describes procedures for 
modifying the inner rear spar web of the wing.
     Airbus Service Bulletin A320-57-1060, Revision 2, dated 
December 16, 1994. This service information describes procedures for a 
cold expansion of all the attachment holes for the forward pintle 
fitting of the main landing gear (MLG), except for the holes that are 
for taper-lok bolts; and for a cold expansion of the holes at the 
actuating cylinder anchorage of the MLG.
     Airbus Mandatory Service Bulletin A320-57-1088, Revision 
04, dated August 6, 2001. This service information describes procedures 
for doing ultrasonic inspections for cracking of the rear spar of the 
wing.
     Airbus Service Bulletin A320-57-1089, Revision 03, dated 
February 9, 2001. This service information describes modification of 
the airplane by accomplishing cold reexpansion of the holes in the 
inner rear spar for the attachment of gear rib 5, forward pintle 
fitting, and actuating cylinder anchorage; and the installation of 
interference fit fasteners in the rear spar and gear rib 5.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSESsection of this 
NPRM.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Costs of Compliance

    We estimate that this proposed AD affects 84 airplanes of U.S. 
registry.
    The actions required by AD 2004-19-11, Amendment 39-13805 (69 FR 
58828, October 1, 2004), and retained in this proposed AD take about 
684 work-hours per product, at an average labor rate of $85 per work-
hour. Required parts cost about $13,644 per product. Based on these 
figures, the estimated cost of the actions that are required by AD 
2004-19-11 is $71,784 per product.
    We also estimate that it would take about 980 work-hours per 
product to comply with the basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour. Required parts would cost 
about $32,727 per product. Based on these figures, we estimate the cost 
of this proposed AD on U.S. operators to be $9,746,268, or $116,027 per 
product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004), and 
adding the following new AD:

Airbus: Docket No. FAA-2015-5811; Directorate Identifier 2014-NM-
158-AD.

(a) Comments Due Date

    We must receive comments by January 11, 2016.

[[Page 74060]]

(b) Affected ADs

    This AD replaces AD 2004-19-11, Amendment 39-13805 (69 FR 58828, 
October 1, 2014).

(c) Applicability

    This AD applies to Airbus Model A320-211, -212, -214, -231, -232, 
and -233 airplanes, certificated in any category, all manufacturer 
serial numbers, except those on which Airbus modification (mod) 24591 
has been embodied in production.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of fatigue cracking of the inner 
rear spar of the wing and also by the determination that the 
modification of the inner rear spar is necessary to address the unsafe 
condition. We are issuing this AD to prevent fatigue cracking of the 
inner rear spar, which may lead to reduced structural integrity of the 
wing and the main landing gear (MLG).

(f) Compliance

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

(g) Retained Modification of Inner Rear Spar Web of the Wing, With 
Change to Acceptable Service Information

    This paragraph restates the requirements of paragraph (a) of AD 
2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004), with a 
change to acceptable service information. For airplanes having 
manufacturer's serial numbers (MSNs) 003 through 008 inclusive, and 010 
through 021 inclusive, except airplanes modified as specified in Airbus 
Service Bulletin A320-57-1089, dated December 22, 1996; Revision 01, 
dated April 17, 1997; Revision 02, dated November 6, 1998; or Revision 
03, dated February 9, 2001: Prior to the accumulation of 12,000 total 
flight cycles, or within 500 flight cycles after June 11, 1993 (the 
effective date of AD 93-08-15, Amendment 39-8563 (58 FR 27923, May 12, 
1993)), whichever occurs later, modify the inner rear spar web of the 
wing in accordance with Airbus Service Bulletin A320-57-1004, Revision 
1, dated September 24, 1992; or Revision 2, dated June 14, 1993. As of 
the effective date of this AD, only Airbus Service Bulletin A320-57-
1004, Revision 2, dated June 14, 1993, may be used for the actions 
required by this paragraph.

(h) Retained Cold Expansion of Holes at Forward Pintle Fitting and 
Actuating Cylinder Anchorage of the Main Landing Gear, With Change to 
Acceptable Service Information

    This paragraph restates the requirements of paragraph (b) of AD 
2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004), with a 
change to acceptable service information. For airplanes having MSNs 002 
through 051 inclusive, except airplanes modified as specified in Airbus 
Service Bulletin A320-57-1089, dated December 22, 1996; Revision 01, 
dated April 17, 1997; Revision 02, dated November 6, 1998; or Revision 
03, dated February 9, 2001: Prior to the accumulation of 12,000 total 
flight cycles, or within 2,000 flight cycles after February 14, 1994 
(the effective date of AD 93-25-13, Amendment 39-8777 (59 FR 1903, 
January 13, 1994)), whichever occurs later, accomplish the requirements 
of paragraphs (h)(1) and (h)(2) of this AD in accordance with Airbus 
Service Bulletin A320-57-1060, dated December 8, 1992; Revision 1, 
dated April 26, 1993; or Revision 2, dated December 16, 1994. As of the 
effective date of this AD, only Airbus Service Bulletin A320-57-1060, 
Revision 2, dated December 16, 1994, may be used for the actions 
required by this paragraph.
    (1) Perform a cold expansion of all the attachment holes for the 
forward pintle fitting of the main landing gear (MLG), except for the 
holes that are for taper-lok bolts.
    (2) Perform a cold expansion of the holes at the actuating cylinder 
anchorage of the MLG.

(i) Retained Repetitive Ultrasonic Inspections for Cracking of the Rear 
Spar of the Wing, With No Changes

    This paragraph restates the requirements of paragraphs (c), (d), 
and (e) of AD 2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 
2004), with no changes. Except for airplanes modified as specified in 
Airbus Service Bulletin A320-57-1089, dated December 22, 1996; Revision 
01, dated April 17, 1997; Revision 02, dated November 6, 1998; or 
Revision 03, dated February 9, 2001: Do the actions specified in 
paragraphs (i)(1) and (i)(2) of this AD.
    (1) Do an ultrasonic inspection for cracking of the rear spar of 
the wing, in accordance with Airbus Service Bulletin A320-57-1088, 
Revision 04, dated August 6, 2001. Inspect at the applicable time 
specified in paragraph 1.E. of Airbus Service Bulletin A320-57-1088, 
Revision 04, dated August 6, 2001, except as required by paragraphs 
(i)(1)(i) and (i)(1)(ii) of this AD.
    (i) For any airplane that has not been inspected but has exceeded 
the applicable specified compliance time in paragraph 1.E. of Airbus 
Service Bulletin A320-57-1088, Revision 04, dated August 6, 2001, as of 
November 5, 2004 (the effective date of AD 2004-19-11, Amendment 39-
13805 (69 FR 58828, October 1, 2004)): Inspect within 18 months after 
November 5, 2004.
    (ii) For any airplane that has been inspected before November 5, 
2004 (the effective date of AD 2004-19-11, Amendment 39-13805 (69 FR 
58828, October 1, 2004): Repeat the inspection within 3,600 flight 
cycles after the most recent inspection.
    (2) Repeat the inspection required by paragraph (i)(1) of this AD 
at intervals not to exceed 3,600 flight cycles or 6,700 flight hours, 
whichever occurs first, until the requirements of paragraph (k) of this 
AD have been done.

(j) Retained Corrective Action for Inspections Required by Paragraphs 
(i)(1) and (i)(2) of This AD, With Specific Delegation Approval 
Language.

    This paragraph restates the requirements of paragraph (f) of AD 
2004-19-11, Amendment 39-13805 (69 FR 58828, October 1, 2004), with 
specific delegation approval language. If any crack is found during any 
inspection required by paragraph (i)(1) or (i)(2) of this AD: Before 
further flight, repair in accordance with a method approved by either 
the Manager, International Branch, ANM-116, FAA, Transport Airplane 
Directorate; or the Direction G[eacute]n[eacute]rale de l'Aviation 
Civile (or its delegated agent); or the European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA). 
Accomplishment of a repair as required by this paragraph does not 
constitute terminating action for the repetitive inspections required 
by paragraph (i)(2) of this AD.

(k) New Requirement of This AD: Modification of Inner Rear Spar

    Before exceeding 48,000 flight cycles or 96,000 flight hours, 
whichever occurs first since first flight of the airplane: modify all 
specified fastener holes in the inner rear spar of the wing, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-57-1089, Revision 03, dated February 9, 2001; except 
where Airbus Service Bulletin A320-57-1089, Revision 03, dated February 
9, 2001, specifies to contact Airbus for certain conditions, before 
further flight, repair using a method approved by the

[[Page 74061]]

Manager, International Branch, ANM-116, Transport Airplane Directorate, 
FAA; or EASA; or Airbus's EASA DOA. Modification of all specified 
fastener holes in the rear spar of the wing terminates the initial and 
repetitive inspections required by paragraphs (i)(1) and (i)(2) of this 
AD. If the modification is done both before the airplane accumulates 
12,000 total flight cycles and before the effective date of this AD, 
the modification also terminates the actions required by paragraphs (g) 
and (h) of this AD.

(l) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (i) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-57-1088, 
Revision 02, dated July 29, 1999; or Revision 03, dated February 9, 
2001, which are not incorporated by reference in this AD.
    (2) This paragraph provides credit for actions required by 
paragraph (k) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-57-1089, 
Revision 02, dated November 6, 1998, which is not incorporated by 
reference in 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: 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].
    (i) 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.
    (ii) AMOCs approved previously in accordance with AD 2004-19-11, 
Amendment 39-13805 (69 FR 58828, October 1, 2004), are approved as 
AMOCs for the corresponding provisions of paragraphs (g) through (j) 
of 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 European Aviation Safety Agency 
(EASA); or Airbus' EASA Design Organization Approval (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 2014-0169, corrected July 22, 
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-2015-5811.
    (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 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 November 17, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-30006 Filed 11-25-15; 8:45 am]
 BILLING CODE 4910-13-P