[Federal Register Volume 70, Number 161 (Monday, August 22, 2005)]
[Proposed Rules]
[Pages 48911-48914]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-16534]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22148; Directorate Identifier 2005-NM-033-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series 
Airplanes; A300 B4-600, B4-600R, and F4-600R Series Airplanes, and C4-
605R Variant F Airplanes (Collectively Called A300-600 Series 
Airplanes); and Airbus Model A310-200 and A310-300 Series Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain Airbus model A300-600 and A310 
series airplanes. The existing AD currently requires repetitive visual 
inspections to detect corrosion on the lower rim area of the fuselage 
rear pressure bulkhead; and follow-on actions, if necessary. This 
proposed AD would require new repetitive inspections for corrosion on 
the rear pressure bulkhead between stringer (STGR) 27 (right hand) and 
STGR27 (left hand), and related investigative/corrective actions if 
necessary. This proposed AD also would require sending a report of 
certain information to the manufacturer. The proposed AD also would add 
airplanes to the applicability of the existing AD. This proposed AD 
results from findings of severe corrosion on airplanes previously 
inspected in accordance with the existing AD. We are proposing this AD 
to detect and correct corrosion at the lower rim area of the fuselage 
rear pressure bulkhead, which could result in reduced structural 
integrity of the bulkhead, and consequent decompression of the cabin.

DATES: We must receive comments on this proposed AD by September 21, 
2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, Room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for Airbus Model A310 service information identified in this 
proposed AD. Contact Jacques Leborgne, Airbus Customer Service 
Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France; fax (+33) 5 61 93 36 14, for Airbus Model A300 service 
information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Include the docket number 
``Docket No. FAA-2005-22148; Directorate Identifier 2005-NM-033-AD'' at 
the beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of the 
proposed AD. We will consider all comments received by the closing date 
and may amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of our 
docket web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    On September 10, 1998, we issued AD 98-19-22, amendment 39-10763 
(63 FR 49656, September 17, 1998), for certain Airbus Model A310 and 
A300-600 series airplanes. That AD requires repetitive visual 
inspections to detect corrosion on the lower rim area of the fuselage 
rear pressure bulkhead; and follow-on actions, if necessary. That AD 
resulted from issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. We issued that 
AD to detect and correct corrosion at the lower rim area of the 
fuselage rear pressure bulkhead, which could result in reduced 
structural integrity of the bulkhead, and consequent decompression of 
the cabin.

Other Relevant Rulemaking

    On June 21, 2001, we issued AD 2001-14-17, amendment 39-12328 (66

[[Page 48912]]

FR 36154, July 11, 2001), for all Airbus Model A300 B2 and B4 series 
airplanes. That AD requires a one-time inspection to detect and correct 
corrosion of the lower bulkhead attachment, and corrective action, if 
necessary. That AD was prompted by reported failure of the rear 
pressure bulkhead on an Airbus Model A300 series airplane during 
flight, which lead to rapid cabin decompression. We issued that AD to 
detect and correct corrosion of the lower bulkhead attachment, which 
could result in reduced structural integrity of the rear pressure 
bulkhead and consequent damage to components of the flight control, 
hydraulic, and auxiliary power unit fuel systems.
    AD 2001-14-17 mandated a one-time inspection within 2 to 4 weeks 
after July 26, 2001 (the effective date of AD 2001-14-17). Based on 
results of this one-time inspection, the manufacturer developed a 
modification for certain Airbus Model A300-600 series airplanes, and 
Model A310 series airplanes; these airplanes are also included in the 
applicability this proposed AD. That Airbus modification is the subject 
of another proposed AD: Docket No. FAA-2005-21343; Directorate 
Identifier 2004-NM-117-AD (70 FR 32547, June 3, 2005).

Actions Since AD 98-19-22 Was Issued

    Since we issued AD 98-19-22, severe corrosion has been found on 
certain airplanes that were previously inspected in accordance with 
that AD. Based on those findings, we have determined that the 
inspection methods in AD 98-19-22 are obsolete and inadequate, and that 
a new inspection program is necessary. Therefore, the actions from AD 
98-19-22 are not retained or repeated in this proposed AD. In addition, 
since we issued AD 98-19-22, we have determined that certain additional 
Airbus Model A300 B2 and A300 B4, and Airbus Model A310-200 and A310-
300 series airplanes would be affected by the actions in this proposed 
AD.

Relevant Service Information

    Airbus has issued the service bulletins in the following table.

                                            Airbus Service Bulletins
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               Airbus model                          Service bulletin                         Date
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A300 B2 and A300 B4 series airplanes......  A300-53-0363.....................  October 27, 2004.
A300-600 series airplanes.................  A300-53-6136.....................  October 27, 2004.
A310-200 and A310-300 series airplanes....  A310-53-2114.....................  October 27, 2004.
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    The service bulletins provide procedures for doing the following 
repetitive inspections for corrosion on the rear pressure bulkhead 
between stringer (STGR) 27 (right hand) and STGR27 (left hand):
     Two special detailed inspections, one before cleaning and 
one after cleaning, of the internal and external surface of the lower 
rim angle in the area of the drainhole (inspection areas AI, AII, AIII, 
and B);
     A detailed visual inspection of the cleat profile splice 
at the airplane centerline (inspection area C); and
     For A300 B2 and A300 B4 series airplanes: an eddy current 
inspection and an X-ray inspection of area D.
    If corrosion is found during these inspections, the service 
bulletins provide procedures for doing several related investigative 
and corrective actions, depending on the inspection area and inspection 
findings. These related investigative and corrective actions are 
described below.
    For all inspection areas where corrosion was found, the service 
bulletins provide procedures for doing the following applicable 
actions, as described in Figure 2, Sheet 2 of the service bulletins:
     If the corrosion is within certain permanent limits 
specified in the service bulletin, repair the paint, repair the 
sealant, and re-install the retainer angle if necessary;
     If the corrosion is within certain temporary limits 
specified in the service bulletin, contact Airbus for repair 
instructions within 6 months or 1 year, depending on the extent of the 
corrosion.
     If the corrosion exceeds certain limits specified in the 
service bulletin, contact Airbus for repair instructions before further 
flight.
    For inspection area AII, the service bulletins provide procedures 
for doing a detailed visual inspection for corrosion of the newly 
visible area. If corrosion is found in area AII during this inspection, 
or if any previous inspection indicates that there may be corrosion in 
area AIII, the service bulletins provide procedures for removing the 
retainer angle and support sealant, doing a detailed visual inspection 
for corrosion, cracks, or cut lines of the newly visible area (inner 
rim angle and cleat profile), and doing the following applicable 
actions based on the inspection results:
     If the corrosion is greater than 5.0 mm to the cleat 
profile, or if no crack is found, remove any corrosion and do the 
applicable corrective action described in Figure 2, Sheet 2 of the 
service bulletins.
     If any cut line or crack is found, the corrective action 
is to contact Airbus for repair instructions.
    If, when accomplishing certain inspections, any corrosion is found 
on or near the fasteners, the service bulletins provide procedures for 
doing a rototest and installing titanium fasteners instead of steel 
fasteners. In addition, the service bulletins specify that operators 
should contact Airbus if any structural repair is necessary.
    The service bulletins also specify that operators should send a 
Record Sheet to the manufacturer related to all inspections and 
findings.
    The DGAC mandated the service information and issued French 
airworthiness directive F-2004-193, dated December 22, 2004, to ensure 
the continued airworthiness of these airplanes in France.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that AD action is 
necessary for airplanes of this type design that are certificated for 
operation in the United States.
    This proposed AD would supersede AD 98-19-22. This proposed AD 
would require accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Among the Proposed AD, the French Airworthiness 
Directive, and the Service Information.''
    This proposed AD also requires that operators report corrosion 
findings to

[[Page 48913]]

Airbus. This information will help determine the extent of the 
corrosion problems in the affected fleets. Based on the results of 
these reports, we may determine that further corrective action is 
warranted.

Differences Among the Proposed AD, the French Airworthiness Directive, 
and the Service Information

    The French airworthiness directive states that any repair for 
detected corrosion must be done within the associated deadlines in 
Figure 2 Sheet 2 of the applicable service bulletin. Those deadlines, 
specified in the ``Temporary Limits for Removal of Corrosion,'' section 
of the figure, range from 6 months to 1 year depending on the extent of 
the corrosion damage. To accomplish these repairs, the service 
bulletins also state that operators should contact Airbus for certain 
repair instructions. However, this proposed AD would require operators 
to repair all detected damage that is within the corrosion limits 
described in the ``Temporary Limits for Removal of Corrosion'' not at 
the time specified in Figure 2 Sheet 2 of the applicable service 
bulletin, but before further flight, and using a method that we, or the 
DGAC (or its delegated agent) approve.
    Although the French airworthiness directive specifies a compliance 
time based on an airplane's ``entry into service,'' this proposed AD 
would specify a compliance time based on ``the date of issuance of the 
original standard airworthiness certificate or the date of issuance of 
the original export certificate of airworthiness.'' This decision is 
based on our determination that ``entry into service'' may be 
interpreted differently by different operators. We find that our 
proposed terminology is generally understood within the industry and 
records will always exist that establish these dates with certainty.
    Although the service bulletins that are mandated by the French 
airworthiness directive specify that operators should send a Record 
Sheet to the manufacturer related to all inspections and findings, this 
proposed AD would require operators only to report corrosion findings.
    These differences have been coordinated with the DGAC.

Clarification of Inspection Terminology

    In this proposed AD, the ``detailed visual inspection'' specified 
in the service bulletins is referred to as a ``detailed inspection.'' 
We have included the definition for a detailed inspection in a note in 
the proposed AD.

Interim Action

    This AD is considered to be interim action. The reports that would 
be required by this proposed AD will enable the manufacturer to obtain 
better insight into the nature, cause, and extent of the corrosion, and 
eventually to develop final action to address the unsafe condition. 
Once final action has been identified, we may consider further 
rulemaking.

Costs of Compliance

    This proposed AD would affect about 190 airplanes of U.S. registry. 
The new proposed actions would take about 10 work hours per airplane, 
at an average labor rate of $65 per work hour. Based on these figures, 
the estimated cost of the new actions specified in this proposed AD for 
U.S. operators is $123,500, or $650 per airplane, per inspection cycle.

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 have 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 that the 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. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-10763 (63 FR 49656, September 17, 1998) and 
adding the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2005-22148; Directorate Identifier 2005-NM-
033-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by September 
21, 2005.

Affected ADs

    (b) This AD supersedes AD 98-19-22, amendment 39-10763.

Applicability

    (c) This AD applies to all airplanes identified in Table 1 of 
this AD, certificated in any category.

[[Page 48914]]



                                 Table 1.--Airbus Airplanes Affected by This AD
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                                             As identified in Airbus Service
               Airbus model                             Bulletin--                          Dated--
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A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C,   A300-53-0363.....................  October 27, 2004.
 B4-103, and B4-203 airplanes.
A300 B4-601, B4-603, B4-620, B4-622, A300   A300-53-6136.....................  October 27, 2004.
 B4-605R, B4-622R, F4-605R, F4-622R, and
 A300 C4-605R Variant F airplanes.
A310-203, -204, -221, -222, -304, -322, -   A310-53-2114.....................  October 27, 2004.
 324, and -325 airplanes.
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Unsafe Condition

    (d) This AD results from findings of severe corrosion on 
airplanes previously inspected in accordance with the existing AD. 
We are issuing this AD to detect and correct corrosion at the lower 
rim area of the fuselage rear pressure bulkhead, which could result 
in reduced structural integrity of the bulkhead, and consequent 
decompression of the cabin.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Service Bulletin Reference

    (f) For the purposes of this AD, the term ``service bulletin'' 
means the accomplishment instructions of the applicable service 
bulletin identified in Table 1 of this AD.

Inspections and Corrective Actions

    (g) Within 60 months since the date of issuance of the original 
standard airworthiness certificate or the date of issuance of the 
original export certificate of airworthiness; or within 18 months 
after the effective date of this AD; whichever is later: Do the 
detailed inspection, special detailed inspections, and any 
applicable eddy current and X-ray inspection, for corrosion on the 
rear pressure bulkhead between stringer (STGR) 27 (right hand) and 
STGR27 (left hand) in accordance with the applicable service 
bulletin, and repeat these inspections thereafter at intervals not 
to exceed 36 months. Do any applicable related investigative and 
corrective actions before further flight in accordance with the 
applicable service bulletin, except as provided by paragraph (h) of 
this AD.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''


    Note 2: For the purposes of this AD, a special detailed 
inspection is: ``An intensive examination of a specific item, 
installation, or assembly to detect damage, failure, or 
irregularity. The examination is likely to make extensive use of 
specialized inspection techniques and/or equipment. Intricate 
cleaning and substantial access or disassembly procedure may be 
required.''

    (h) If any corrosion damage or crack is found during any 
inspection or corrective action required by this AD, and the service 
bulletin recommends contacting Airbus for repair instructions: 
Before further flight, repair in accordance with a method approved 
by the Manager, International Branch, ANM-116, FAA, Transport 
Airplane Directorate.

Reporting

    (i) Submit a report of corrosion found during the inspections 
required by paragraph (g) of this AD to SE-A21, AIRBUS CUSTOMER 
SERVICES DIRECTORATE, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France, at the applicable time specified in paragraph (i)(1) 
or (i)(2) of this AD. The report must include the inspection type, a 
description of any corrosion found, the airplane serial number, and 
the number of landings and flight hours on the airplane. Under the 
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et 
seq.), the Office of Management and Budget (OMB) has approved the 
information collection requirements contained in this AD and has 
assigned OMB Control Number 2120-0056.
    (1) If the inspection was done after the effective date of this 
AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was accomplished prior to the effective 
date of this AD: Submit the report within 30 days after the 
effective date of this AD.

Alternative Methods of Compliance (AMOCs)

    (j)(1) The Manager, International Branch, ANM-116, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) AMOCs approved previously according to AD 98-19-22, 
amendment 39-10763, are not approved as AMOCs for this AD.

Related Information

    (k) French airworthiness F-2004-193 dated December 22, 2004, 
also addresses the subject of this AD.

    Issued in Renton, Washington, on August 11, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-16534 Filed 8-19-05; 8:45 am]
BILLING CODE 4910-13-P