
[Federal Register: June 24, 2008 (Volume 73, Number 122)]
[Proposed Rules]               
[Page 35601-35603]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr24jn08-17]                         

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0670; Directorate Identifier 2007-NM-339-AD]
RIN 2120-AA64

 
Airworthiness Directives; Airbus Model A318, A319, A320, and A321 
Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed AD results from mandatory 
continuing airworthiness information (MCAI) originated by an aviation 
authority of another country to identify and correct an unsafe 
condition on an aviation product. The MCAI describes the unsafe 
condition as:

    Damage to the lower lateral fittings of the 80VU rack * * * 
[and] damage to the lower central support fitting * * *.
    In the worst case scenario a complete failure of the 80VU 
fittings in combination with a high load factor or strong vibration 
could lead to failure of the rack structure and/or computers or 
rupture/disconnection of the cable harnesses to one or more 
computers located in the 80VU. This rack contains computers for 
Flight Controls, Communication and Radio-navigation. These functions 
are duplicated across other racks but during critical phases of 
flight the multiple system failures/re-configuration may constitute 
an unsafe condition.
* * * * *
The proposed AD would require actions that are intended to address the 
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by July 24, 2008.

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 W12-40, 1200 New 
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office 
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: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2141; 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-2008-0670; 
Directorate Identifier 2007-NM-339-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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2007-0276, dated October 26, 2007 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Damage to the lower lateral fittings of the 80VU rack, typically 
elongated holes, migrated bushes [bushings], and/or missing bolts 
have been reported in-service. In addition damage to the lower 
central support fitting (including cracking) has been reported.
    In the worst case scenario a complete failure of the 80VU 
fittings in combination with a high load factor or strong vibration 
could lead to failure of the rack structure and/or computers or 
rupture/disconnection of the cable harnesses to one or more 
computers located in the 80VU. This rack contains computers for 
Flight Controls, Communication and Radio-navigation. These functions 
are duplicated across other racks but during critical phases of 
flight the multiple system failures/re-configuration may constitute 
an unsafe condition.
    This Airworthiness Directive (AD) mandates the repetitive 
inspection of the lower lateral 80VU fittings for damage and the 
inspection of the lower central 80VU support for damage and 
cracking, and the associated corrective actions as necessary with 
more restrictive actions than defined in Airbus Service Bulletin 
(SB) A320-25A1555 at its original issue.
    The new requirements defined in this AD will be introduced in 
revision 1 of SB A320-25A1555.


[[Page 35602]]


The associated corrective actions include repair or replacement of the 
lower lateral fittings and/or central support. Replacing the 80VU 
support fittings eliminates the need for the repetitive inspection of 
the lower lateral fittings, and extends the repetitive interval for the 
lower central support. You may obtain further information by examining 
the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued Service Bulletins A320-25A1555, dated June 14, 
2007; and A320-25-1557, dated June 14, 2007. The actions described in 
this service information are intended to correct the unsafe condition 
identified in the MCAI. The compliance times for doing the corrective 
actions are either before further flight, or within 4,500 flight cycles 
with repetitive inspections at intervals not to exceed 750 flight 
cycles until the repair is accomplished.

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 AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a Note within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 678 products of U.S. registry. We also estimate that 
it would take about 82 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $80 per 
work-hour. Required parts would cost about $2,592 per product. Where 
the service information lists required parts costs that are covered 
under warranty, we have assumed that there will be no charge for these 
costs. As we do not control warranty coverage for affected parties, 
some parties may incur costs higher than estimated here. Based on these 
figures, we estimate the cost of the proposed AD on U.S. operators to 
be $6,205,056, or $9,152 per product.

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); and
    3. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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

    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]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Airbus: Docket No. FAA-2008-0670; Directorate Identifier 2007-NM-
339-AD.

Comments Due Date

    (a) We must receive comments by July 24, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A318-111, A318-112, A319-
111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-132, 
A319-133, A320-111, A320-211, A320-212, A320-214, A320-231, A320-
232, A320-233, A321-111, A321-112, A321-131, A321-211, A321-212, 
A321-213, A321-231, and A321-232 airplanes, certificated in any 
category, except airplanes on which Airbus Modification 34804 has 
been embodied in production.

Subject

    (d) Air Transport Association (ATA) of America Code 25: 
Equipment/Furnishings.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    Damage to the lower lateral fittings of the 80VU rack, typically 
elongated holes, migrated bushes [bushings], and/or missing bolts 
have been reported in-service. In addition, damage to the lower 
central support fitting (including cracking) has been reported.
    In the worst case scenario a complete failure of the 80VU 
fittings in combination with a high load factor or strong vibration 
could lead to failure of the rack structure and/or computers or 
rupture/disconnection of the cable harnesses to one or more 
computers located in the 80VU. This rack contains computers for 
Flight Controls, Communication and Radio-navigation. These functions 
are duplicated across other racks but during critical phases of 
flight the multiple system failures/re-configuration may constitute 
an unsafe condition.
    This Airworthiness Directive (AD) mandates the repetitive 
inspection of the lower lateral 80VU fittings for damage and the 
inspection of the lower central 80VU

[[Page 35603]]

support for damage and cracking, and the associated corrective 
actions as necessary with more restrictive actions than defined in 
Airbus Service Bulletin (SB) A320-25A1555 at its original issue.
    The new requirements defined in this AD will be introduced in 
revision 1 of SB A320-25A1555.

The associated corrective actions include repair or replacement of 
the lower lateral fittings and/or central support. Replacing the 
80VU support fittings eliminates the need for the repetitive 
inspection of the lower lateral fittings, and extends the repetitive 
interval for the lower central support.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Prior to the accumulation of 24,000 total flight cycles, or 
within 500 flight cycles after the effective date of this AD, 
whichever occurs later: Do a special detailed inspection of the 80VU 
rack lower lateral fittings for damage (e.g., broken fitting, 
missing bolts, migrated bushings, material burr, or rack in contact 
with the fitting) of the 80VU rack lower lateral fittings in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-25A1555, dated June 14, 2007. Except as provided by 
paragraph (f)(2) of this AD, repeat the inspection thereafter at the 
interval specified in paragraph (f)(1)(i) or (f)(1)(ii) of this AD, 
as applicable. Replacing the 80VU lower lateral fittings in 
accordance with Airbus Service Bulletin A320-25-1557, dated June 14, 
2007, terminates the inspection requirements of this paragraph.
    (i) If the 80VU rack lower lateral fittings have not been 
repaired in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-25A1555, dated June 14, 2007, repeat 
the inspection thereafter at intervals not to exceed 4,500 flight 
cycles.
    (ii) If the 80VU rack lower lateral fittings have been repaired 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-25A1555, dated June 14, 2007, repeat the inspection 
thereafter at intervals not to exceed 24,000 flight cycles.
    (2) If any damage is found during any inspection required by 
paragraph (f)(1) of this AD, do all applicable corrective actions 
(inspection and/or repair) in accordance with the Accomplishment 
Instructions and timeframes given in Airbus Service Bulletin A320-
25A1555, dated June 14, 2007.
    (3) Prior to the accumulation of 24,000 total flight cycles, or 
within 500 flight cycles after the effective date of this AD, 
whichever occurs later: Do a special detailed inspection of the 80VU 
rack lower central support for cracking in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-25A1555, 
dated June 14, 2007. Except as provided by paragraph (f)(4) of this 
AD, repeat the inspection thereafter at the interval specified in 
paragraph (f)(3)(i) or (f)(3)(ii) of this AD, as applicable.
    (i) If the 80VU rack lower central support has not been repaired 
or replaced in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-25A1555, dated June 14, 2007; or Airbus 
Service Bulletin A320-25-1557, dated June 14, 2007; repeat the 
inspection thereafter at the interval specified in paragraph 
(f)(3)(i)(A) or (f)(3)(i)(B) of this AD, as applicable.
    (A) For airplanes on which the lower central support has 
accumulated more than 30,000 total flight cycles as of the effective 
date of this AD: At intervals not to exceed 500 flight cycles.
    (B) For airplanes on which the lower central support has 
accumulated 30,000 total flight cycles or fewer as of the effective 
date of this AD: At intervals not to exceed 4,500 flight cycles, 
without exceeding 30,750 total flight cycles for the first 
repetitive inspection.
    (ii) If the 80VU rack lower central support has been repaired or 
replaced in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-25A1555, dated June 14, 2007; or Airbus 
Service Bulletin A320-25-1557, dated June 14, 2007; repeat the 
inspection thereafter at intervals not to exceed 24,000 flight 
cycles.
    (4) If any crack is found during any inspection required by 
paragraph (f)(3) of this AD, do the action in paragraph (f)(4)(i) or 
(f)(4)(ii) of this AD, as applicable.
    (i) If the crack length is more than 40 mm on the front or the 
rear sheet of the lower central support, as shown in Figure 3, Sheet 
2 of Airbus Service Bulletin A320-25A1555, dated June 14, 2007, or 
if any crack is found on the upper sheet of the lower central 
support as shown in Figure 3, Sheet 3 of Airbus Service Bulletin 
A320-25A1555, dated June 14, 2007: Before further flight, repair or 
replace the lower central support in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-25A1555, 
dated June 14, 2007; or Airbus Service Bulletin A320-25-1557, dated 
June 14, 2007; as applicable.
    (ii) If the crack length is 40 mm or less on the front or the 
rear sheet, as specified in Figure 3, Sheet 2 of Service Bulletin 
A320-25A1555, dated June 14, 2007: Within 20 months or 4,500 flight 
cycles after the crack finding, whichever occurs first, repair or 
replace the lower central support in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-25A1555, 
dated June 14, 2007; or A320-25-1557, dated June 14, 2007, as 
applicable. Until the repair or replacement of the lower central 
support is accomplished, repeat the inspection required by paragraph 
(f)(3) of this AD thereafter at intervals not to exceed 500 flight 
cycles.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, ANM-
116, International Branch, Transport Airplane Directorate, FAA, has 
the authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. Send information to ATTN: Tim 
Dulin, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 227-2141; fax (425) 227-1149. Before 
using any approved AMOC on any airplane to which the AMOC applies, 
notify your appropriate principal inspector (PI) in the FAA Flight 
Standards District Office (FSDO), or lacking a PI, your local FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2007-0276, dated October 26, 2007; Airbus 
Service Bulletin A320-25A1555, dated June 14, 2007; and Airbus 
Service Bulletin A320-25-1557, dated June 14, 2007, for related 
information.

    Issued in Renton, Washington, on June 8, 2008.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-14184 Filed 6-23-08; 8:45 am]

BILLING CODE 4910-13-P
