[Federal Register Volume 69, Number 135 (Thursday, July 15, 2004)]
[Proposed Rules]
[Pages 42363-42365]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-16031]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18603; Directorate Identifier 2003-NM-14-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) for certain Model A310; and Model A300 B4-600, A300 B4-
600R, and A300 F4-600R (collectively called A300-600) series airplanes. 
That AD currently requires modifying the ram air turbine (RAT) by 
replacing the ejection jack. This proposed AD would require a one-time 
inspection of the RAT ejection jack to determine the part number, and 
further investigative and corrective actions if necessary. This 
proposed AD is prompted by the discovery of a rupture in the housing of 
one of the RAT ejection jacks installed as specified in the existing 
AD. We are proposing this AD to prevent rupture of the housing of the 
RAT ejection jack due to overpressure in the jack caused by overfilling 
the hydraulic fluid, and consequent failure of the RAT ejection jack. 
Failure of the ejection jack could result in a lack of hydraulic 
pressure or electrical power in an emergency.

DATES: We must receive comments on this proposed AD by August 16, 2004.

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.
    You can get the service information identified in this proposed AD 
from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France.
    You may examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., room PL-401, on 
the plaza level of the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer; 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Docket Management System (DMS)

    The FAA has implemented new procedures for maintaining AD dockets 
electronically. As of May 17, 2004, new AD actions are posted on DMS 
and assigned a docket number. We track each action and assign a 
corresponding directorate identifier. The DMS AD docket number is in 
the form ``Docket No. FAA-2004-99999.'' The Transport Airplane 
Directorate identifier is in the form ``Directorate Identifier 2004-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier 
(``Old Docket Number'') as a cross-reference for searching purposes.

Comments Invited

    We invite you to submit any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2004-18603; 
Directorate Identifier 2003-NM-14-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.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications that affect you. You can get more information about 
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.

Examining the Docket

    You may examine the AD docket 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

[[Page 42364]]

the AD docket shortly after the DMS receives them.

Discussion

    On June 21, 2001, we issued AD 2001-13-16, amendment 39-12297 (66 
FR 34798, July 2, 2001), for certain Model A310 and Model A300 B4-600, 
A300 B4-600R, and A300 F4-600R (collectively called A300-600) series 
airplanes. That AD requires replacing the ejection jack on the ram air 
turbine (RAT). That AD was prompted by the discovery of an anomaly 
during production, and follow-up analysis that showed that the nut at 
the end of the ejection jack piston rod had insufficient thread 
engagement to absorb impact loads when the RAT was deployed at high 
speed. We issued that AD to prevent loss of ability to properly 
restrain the movement of the RAT and possible consequent damage to the 
RAT itself and to other airplane components. In the event of an 
emergency, failure of the RAT ejection jack could result in a lack of 
hydraulic pressure or electrical power on the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2001-13-16, the Direction Generale de l'Aviation 
Civile (DGAC), which is the airworthiness authority for France, has 
notified us that, during a routine inspection, a rupture was discovered 
in the housing of one of the RAT ejection jacks installed as specified 
in AD 2001-13-16. Investigation revealed that a certain batch of 
ejection jacks were serviced incorrectly, which may have led to 
overfilling of the ejection jacks and overpressure in the ejection 
jack. This condition, if not corrected, could result in a rupture of 
the housing of the RAT ejection jack, leading to failure of the RAT 
ejection jack. In the event of an emergency, failure of the RAT 
ejection jack could result in a lack of hydraulic pressure or 
electrical power.

Relevant Service Information

    Airbus has issued Service Bulletins A300-29-6050, Revision 02, 
dated April 16, 2003 (for Model A300-600 series airplanes); and A310-
29-2088, Revision 01, dated February 3, 2003 (for Model A310 series 
airplanes). The service bulletins describe procedures for a one-time 
inspection of the RAT ejection jack to determine the part number, and 
applicable related investigative and corrective actions. The 
investigative and corrective actions include determining the serial 
number of the RAT ejection jack; measuring the fluid level of the 
ejection jack, if the serial number is one of the affected batch; and 
servicing the fluid level, or replacing the RAT ejection jack with a 
new RAT ejection jack, as applicable. We have determined that 
accomplishing the actions specified in the service information will 
adequately address the unsafe condition. The DGAC mandated these 
service bulletins and issued French airworthiness directive 2002-
638(B), dated December 24, 2002, to ensure the continued airworthiness 
of these airplanes in France.
    The Airbus service bulletins refer to Hamilton Sundstrand Service 
Bulletin ERPS03/04EJ-29-2, dated May 8, 2002, as an additional source 
of service information for identifying subject RAT ejection jacks and 
performing the applicable related investigative and corrective actions 
described previously.

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. According 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.
    Therefore, we are proposing to supersede AD 2001-13-16. This 
proposed AD would continue to require modifying the RAT by replacing 
the RAT ejection jack with a new, improved RAT ejection jack. This 
proposed AD would also require a one-time inspection of the RAT 
ejection jack to determine the part number, and further investigative 
and corrective actions if necessary. The proposed AD would require you 
to use the service information described previously to perform these 
actions, except as discussed under ``Difference Between the Proposed AD 
and Service Information.''

Difference Between the Proposed AD and Service Information

    Although the Accomplishment Instructions of the Airbus and Hamilton 
Sundstrand service bulletins describe procedures for submitting 
inspection results, this proposed AD would not require that action.

Change to Existing AD

    This proposed AD would retain all requirements of AD 2001-13-16. 
Since AD 2001-13-16 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                          Corresponding  requirement in
     Requirement in AD  2001-13-16               this proposed AD
------------------------------------------------------------------------
Paragraph (a)..........................  Paragraph (f).
Paragraph (b)..........................  Paragraph (g).
------------------------------------------------------------------------

    We have also revised the applicability of the existing AD to 
identify model designations as published in the most recent type 
certificate data sheet for the affected models.

Costs of Compliance

    AD 2001-13-16 affects about 117 airplanes of U.S. registry. The 
actions that are currently required by AD 2001-13-16 and retained in 
this proposed AD take about 6 work hours per airplane, at an average 
labor rate of $65 per work hour. There is no charge for required parts. 
Based on these figures, the estimated cost of the currently required 
actions for U.S. operators is $45,630, or $390 per airplane.
    This proposed AD would affect approximately 149 airplanes of U.S. 
registry. The new proposed inspection would take about 1 work hour 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 $9,685, or $65 per airplane.

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

[[Page 42365]]

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 FAA amends Sec.  39.13 by removing amendment 39-12297 (66 FR 
34798, July 2, 2001) and adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2004-18603; Directorate Identifier 2003-NM-
14-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this AD action by August 16, 2004.

Affected ADs

    (b) This AD supersedes AD 2001-13-16, amendment 39-12297 (66 FR 
34798, July 2, 2001).

Applicability

    (c) This AD applies to Airbus Model A310, and A300 B4-600, B4-
600R, C4 605R Variant F, and F4-600R (collectively called A300-600) 
series airplanes; certificated in any category; as listed in Airbus 
Service Bulletin A300-29-6050, Revision 02, dated April 16, 2003; or 
A310-29-2088, Revision 01, dated February 3, 2003.

Unsafe Condition

    (d) This AD was prompted by the discovery of a rupture in the 
housing of one of the RAT ejection jacks installed as specified in 
the existing AD. We are issuing this AD to prevent rupture of the 
housing of the RAT ejection jack due to overpressure in the jack 
caused by overfilling the hydraulic fluid, and consequent failure of 
the RAT ejection jack. Failure of the ejection jack could result in 
a lack of hydraulic pressure or electrical power in an emergency.

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.

Requirements of AD 2001-13-16

Modification

    (f) For airplanes on which Airbus Modification 12259 has not 
been accomplished: Within 34 months after August 6, 2001 (the 
effective date of AD 2001-13-16, amendment 39-12297), modify the RAT 
per Airbus Service Bulletin A310-29-2086, Revision 01 (for Model 
A310 series airplanes), or A300-29-6048, Revision 01 (for Model 
A300-600 series airplanes), both dated July 12, 2000, as applicable.


    Note 1: Modification of the RAT accomplished prior to August 6, 
2001, in accordance with Airbus Service Bulletin A310-29-2086 or 
A300-29-6048, both dated April 6, 2000, as applicable, is considered 
acceptable for compliance with the action specified in paragraph (f) 
of this AD.

Parts Installation

    (g) As of August 6, 2001, no person may install on an airplane 
an ejection jack, part number 730820, unless it has been modified 
per paragraph (f) of this AD.


    Note 2: Airbus Service Bulletin A310-29-2086 and A300-29-6048, 
both Revision 01, refer to Hamilton Sundstrand Service Bulletin No. 
ERPS03/04EJ-29-1, as an additional source of service information for 
accomplishment of the modification of the RAT and testing of the 
modified RAT.

New Requirements of This AD

Inspection

    (h) Within 2,500 flight hours after the effective date of this 
AD: Inspect the RAT ejection jack to determine the part number (P/
N), in accordance with the Accomplishment Instructions of the 
applicable Airbus Service Bulletin listed in Table 1 of this AD. If 
the P/N can be determined and is neither 772652 nor 772654, no 
further action is required by this paragraph.

                      Table 1.--Service Information
------------------------------------------------------------------------
    For this  airplane  model and
              series--                     Airbus service bulletin--
------------------------------------------------------------------------
A300-600............................  A300-29-6050, Revision 02, dated
                                       April 16, 2003.
A310................................  A310-29-2088, Revision 01, dated
                                       February 3, 2003.
------------------------------------------------------------------------


    Note 3: Airbus Service Bulletins A300-29-6050 and A310-29-2088 
refer to Hamilton Sundstrand Service Bulletin ERPS03/04EJ-29-2, 
dated May 8, 2002, as an additional source of service information 
for identifying subject RAT ejection jacks and performing the 
applicable related investigative and corrective actions.

Related Investigative and Corrective Actions (If Necessary)

    (i) If the P/N on the RAT ejection jack is either 772652 or 
772654, or if the P/N cannot be determined: Before further flight, 
accomplish all applicable related investigative and corrective 
actions in accordance with the Accomplishment Instructions of the 
applicable Airbus Service Bulletin listed in Table 1 of this AD.

Actions Accomplished Previously

    (j) Inspections and related investigative and corrective actions 
done before the effective date of this AD in accordance with Airbus 
Service Bulletin A300-29-6050 (for Model A300-600 series airplanes); 
or A310-29-2088 (for Model A310 series airplanes); both dated July 
23, 2002; as applicable; are acceptable for compliance with the 
corresponding actions required by paragraphs (h) and (i) of this AD.

Alternative Methods of Compliance (AMOCs)

    (k) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.

Related Information

    (l) French airworthiness directive 2002-638(B), dated December 
24, 2002, also addresses the subject of this AD.

    Issued in Renton, Washington, on July 8, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-16031 Filed 7-14-04; 8:45 am]
BILLING CODE 4910-13-P