[Federal Register Volume 71, Number 208 (Friday, October 27, 2006)]
[Rules and Regulations]
[Pages 62888-62890]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-17657]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25088; Directorate Identifier 2006-NM-085-AD; 
Amendment 39-14799; AD 2006-22-02]
RIN 2120-AA64


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

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

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Airbus Model A300-600 series airplanes. 
That AD currently requires an inspection for evidence of chafing 
between the hydraulic flexible hose and the ram air turbine (RAT) hub, 
and related investigative and corrective actions if necessary. This new 
AD extends the applicability to include all Model A300-600 series 
airplanes that are equipped with a certain RAT. This AD results from 
reports of holes in the RAT hub cover. We are issuing this AD to 
prevent a hole in the RAT hub cover. A hole in the RAT hub cover could 
allow water to enter the RAT governing mechanism, freeze during flight, 
and jam the governing mechanism. In addition, the metal particles that 
result from chafing between the hydraulic flexible hose and the RAT 
could mix with the lubricant grease and degrade the governing 
mechanism. In an emergency, a jammed or degraded RAT could result in 
its failure to deploy, loss of hydraulic pressure or electrical power 
to the airplane, and consequent reduced controllability of the 
airplane.

DATES: This AD becomes effective December 1, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of December 1, 
2006.
    On August 26, 2005 (70 FR 42267, July 22, 2005), the Director of 
the Federal Register approved the incorporation by reference of Airbus 
Service Bulletin A300-29-6054, Revision 01, excluding Appendix 01, 
dated November 4, 2004.

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

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (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 street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2005-15-05, amendment 
39-14194 (70 FR 42267, July 22, 2005). The existing AD applies to 
certain Airbus Model A300-600 series airplanes. That NPRM was published 
in the Federal Register on June 21, 2006 (71 FR 35575). That NPRM 
proposed to require an inspection for evidence of chafing between the 
hydraulic flexible hose and the ram air turbine (RAT) hub, and related 
investigative and corrective actions if necessary.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the NPRM.

Request To Provide Chafe Limits in the AD

    Air Transport Association (ATA) of America, on behalf of its 
member, FedEx, requests that we provide the chafe limits for the RAT 
hub cover in the AD to ensure clarity for compliance purposes. FedEx 
points out that Airbus Service Bulletin A300-29-6054, Revision 02, 
dated January 12, 2006 (the appropriate source of service information 
for accomplishing the required actions), specifies evaluating any 
damage to the hub cover in accordance with Hamilton Sundstrand 
Component Maintenance Manual

[[Page 62889]]

(CMM) 29-21-21. FedEx reviewed CMM 29-21-21 and did not find any 
discussion of chafing damage. FedEx points out that the CMM addresses 
only dent limits and scratches. FedEx also points out that, for 
scratches, the CMM gives repair instructions for those under 0.005 inch 
in depth or requires replacement, but the CMM gives no serviceable 
limit. FedEx would like to know if it can assume, since chafing is not 
specifically addressed in the CMM, that the RAT must be removed 
immediately and replaced, or if the scratch damage criteria apply. 
FedEx queried both Hamilton Sundstrand and Airbus for clarification, 
but states that no publications have yet been revised to provide a 
reasonable amount of clarity.
    Since we issued the NPRM, Hamilton Sundstrand incorporated into CMM 
29-21-21, dated March 6, 2006, values that clarify the damage limits 
for the RAT hub cover, as follows:
     Check criteria, page 505 (check number 35); and
     Repair, page 601 (repair number 16).
    CMM 29-21-21 and Airbus Service Bulletin A300-29-6054, Revision 02, 
state that all external scores, smooth dents, and abrasions that do not 
include cracks, and that meet the requirement of Flag 1 and Flag 2 of 
CMM 29-21-21, Figure 818, are acceptable and do not require further 
action. If damage exceeds the limits provided in Figure 818 of the CMM, 
the CMM specifies that the cover should be repaired in accordance with 
CMM 29-21-21, repair number 13. Otherwise, the CMM specifies that the 
RAT be replaced. Both the CMM and paragraph (f) of the NPRM specify 
that repair and replacement must be done before further flight. 
However, operators may request approval of an alternative method of 
compliance (AMOC) by following the procedures in paragraph (h) of this 
AD. Since the CMM is secondary reference material, no change to the 
final rule is needed.

Request To Change Compliance Time

    ATA, on behalf of its member, FedEx, requests that the time 
allotted for operators to accomplish the inspections be increased from 
2,500 flight hours to 3,500 flight hours after the effective date of 
this AD. FedEx states that its A300 maintenance program currently 
requires heavy maintenance (C-check) to be performed at the earlier of 
every 3,500 flight hours or 30 months. FedEx states that, since this 
RAT inspection has the potential for component replacement that cannot 
be performed at most line maintenance stations because of test 
equipment requirements, the longer compliance time would help FedEx to 
align the work with currently scheduled heavy maintenance checks. This 
longer compliance time would allow FedEx an additional 200 days 
(according to its utilization rate) to do the inspection in a heavy 
maintenance environment. FedEx notes that it began doing the 
inspections specified in the NPRM in June 2006, but has yet to 
experience any chafing problems.
    We do not agree with the commenter's request to change the 
compliance time. In developing an appropriate compliance time for this 
action, we considered the urgency associated with the subject unsafe 
condition, the availability of required parts, and the practical aspect 
of accomplishing the required modification within a period of time that 
corresponds to the normal scheduled maintenance for most affected 
operators. However, operators may request approval of an alternative 
method of compliance (AMOC) by following the procedures in paragraph 
(h) of this AD to request a different compliance time if the request 
includes data that prove that the new compliance time would provide an 
acceptable level of safety. We have not changed the final rule in this 
regard.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been submitted, and determined that air safety and 
the public interest require adopting the AD as proposed.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD.

 
                                                 Estimated Costs
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                                                                                  Number of U.S.-
             Action                 Work hours     Average labor     Cost per       registered      Fleet cost
                                                   rate per hour     airplane        airplanes
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Inspection......................               1             $80             $80             120          $9,600
Rework binding..................               1              80              80             120           9,600
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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 have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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 AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

[[Page 62890]]

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14194 (70 FR 42267, July 22, 2005) and by adding 
the following new airworthiness directive (AD):

2006-22-02 Airbus: Amendment 39-14799. Docket No. FAA-2006-25088; 
Directorate Identifier 2006-NM-085-AD.

Effective Date

    (a) This AD becomes effective December 1, 2006.

Affected ADs

    (b) This AD supersedes AD 2005-15-05.

Applicability

    (c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, 
B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F 
airplanes; certificated in any category; equipped with a Hamilton 
Sundstrand Ram Air Turbine (RAT).

Unsafe Condition

    (d) This AD results from reports of holes in the ram air turbine 
(RAT) hub cover. We are issuing this AD to prevent a hole in the RAT 
hub cover. A hole in the RAT hub cover could allow water to enter 
the RAT governing mechanism, freeze during flight, and jam the 
governing mechanism. In addition, the metal particles that result 
from chafing between the hydraulic flexible hose and the RAT could 
mix with the lubricant grease and degrade the governing mechanism. 
In an emergency, a jammed or degraded RAT could result in its 
failure to deploy, loss of hydraulic pressure or electrical power to 
the airplane, and consequent reduced controllability of the 
airplane.

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.

Restatement of the Requirements of AD 2005-15-05 With Compliance Times 
for New Airplanes

Inspection and Related Investigative/Corrective Actions

    (f) At the applicable time specified in paragraph (f)(1) or 
(f)(2) of this AD: Do a one-time detailed inspection for evidence of 
chafing between the hydraulic flexible hose and the RAT hub, and any 
applicable related investigative and corrective actions, by 
accomplishing all of the applicable actions specified in the 
Accomplishment Instructions of Airbus Service Bulletin A300-29-6054, 
Revision 01, excluding Appendix 01, dated November 4, 2004; or 
Revision 02, excluding Appendix 01, dated January 12, 2006. After 
the effective date of this AD, only Revision 02 of the service 
bulletin may be used. Any applicable corrective actions must be 
accomplished before further flight. Where the service bulletins 
specify to submit certain information to the manufacturer, and to 
submit damaged RATs to the vendor or a repair station, this AD does 
not include those requirements.
    (1) For airplanes having serial numbers (S/Ns) 0812, 0813, 0815 
through 0818 inclusive, 0821 through 0828 inclusive, and 0836 
through 0838 inclusive: Within 2,500 flight hours after August 26, 
2005 (the effective date of AD 2005-15-05).
    (2) For airplanes not identified in paragraph (f)(1) of this AD: 
Within 2,500 flight hours after the effective date 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.''

Actions Accomplished Previously

    (g) Actions accomplished before the effective date of this AD, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-29-6054, excluding Appendix 01, dated June 8, 2004, 
are acceptable for compliance with the corresponding actions 
specified in this AD.

Alternative Methods of Compliance (AMOCs)

    (h)(1) 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.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.
    (3) AMOCs approved previously in accordance with AD 2005-15-05 
are approved as AMOCs for the corresponding provisions of this AD.

Related Information

    (i) French airworthiness directive F-2006-035, dated February 1, 
2006, also addresses the subject of this AD.

Material Incorporated by Reference

    (j) You must use Airbus Service Bulletin A300-29-6054, Revision 
01, excluding Appendix 01, dated November 4, 2004; or Airbus Service 
Bulletin A300-29-6054, Revision 02, excluding Appendix 01, dated 
January 12, 2006; to perform the actions that are required by this 
AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of Airbus Service Bulletin A300-29-6054, 
Revision 02, excluding Appendix 01, dated January 12, 2006, in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) On August 26, 2005 (70 FR 42267, July 22, 2005), the 
Director of the Federal Register approved the incorporation by 
reference of Airbus Service Bulletin A300-29-6054, Revision 01, 
excluding Appendix 01, dated November 4, 2004.
    (3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France, for a copy of this service information. You may 
review copies at the Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on October 11, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-17657 Filed 10-26-06; 8:45 am]
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