[Federal Register Volume 73, Number 198 (Friday, October 10, 2008)]
[Proposed Rules]
[Pages 60203-60206]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-24151]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1082; Directorate Identifier 2007-NM-337-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 Airplanes; Model A300 
B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and 
C4-605R Variant F Airplanes (Collectively Called A300-600 Series 
Airplanes); and Model A310 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 all of the airplanes identified above. 
The existing AD currently requires revising the FAA-approved 
maintenance program to include a new airplane maintenance manual task 
that specifies a detailed inspection after each ram air turbine (RAT) 
retraction. That existing AD also currently requires, for certain 
airplanes, a one-time inspection to detect breaks in the bottom flange 
fitting of the RAT and corrective actions, if necessary; for certain 
airplanes, an adjustment of the ejection jack; and, for certain other 
airplanes, replacement of the aluminum part with an improved steel 
part. This proposed AD also would continue to require certain actions 
for additional airplanes and would revise the FAA-approved maintenance 
program to include procedures for replacing the RAT swivel coupling 
fork fitting with a new steel part only. This proposed AD results from 
a report that an additional swivel coupling of the RAT yoke fitting was 
found cracked while accomplishing the requirements of the existing AD. 
We are proposing this AD to prevent misrigging of the ejection jack of 
the RAT and to ensure removal of any RAT yoke fitting made from 
aluminum material. Such conditions could result in a broken or cracked 
swivel coupling and consequent failure of the RAT yoke fitting, which 
could result in the loss of RAT function and possible loss of critical 
flight control systems in the event of certain emergency situations.

DATES: We must receive comments on this proposed AD by November 10, 
2008.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Airbus, 1 
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1138; 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-2008-1082; 
Directorate Identifier 2007-NM-337-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 because of 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

[[Page 60204]]

substantive verbal contact we receive about this proposed AD.

Discussion

    On January 24, 2007, we issued AD 2007-03-09, amendment 39-14920 
(72 FR 5157, February 5, 2007), for all Airbus Model A300 airplanes; 
Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, 
F4-622R, and C4-605R variant F airplanes (collectively called A300-600 
series airplanes); and Model A310 airplanes. That AD requires revising 
the FAA-approved maintenance program to include a new airplane 
maintenance manual task that specifies a detailed inspection after each 
ram air turbine (RAT) retraction. That AD also requires, for certain 
airplanes, a one-time inspection to detect breaks in the bottom flange 
fitting of the RAT and corrective actions, if necessary; for certain 
airplanes, an adjustment of the ejection jack; and, for certain other 
airplanes, replacement of the aluminum part with an improved steel 
part. That AD resulted from a report indicating that the swivel 
coupling of the RAT yoke fitting was found broken (due to a static 
overload as a result of the ejection jack of the RAT being misrigged). 
We issued that AD to prevent failure of the RAT yoke fitting, which 
could result in the loss of RAT function and possible loss of critical 
flight control systems in the event of certain emergency situations.

Actions Since Existing AD Was Issued

    Since we issued AD 2007-03-09, European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community, informed us that an additional swivel coupling of 
the RAT yoke fitting was found cracked while accomplishing the 
requirements of that AD. Investigation revealed that the crack was 
initiated by a stress-corrosion phenomenon on the aluminum material.
    Misrigging of the ejection jack of the RAT or a RAT yoke fitting 
that is made from aluminum material, if not corrected, could result in 
a broken or cracked swivel coupling and consequent failure of the RAT 
yoke fitting. This condition could result in the loss of RAT function 
and possible loss of critical flight control systems in the event of 
certain emergency situations.
    EASA has also informed us that certain Model A310 and A300-600 
series airplanes equipped with Hamilton Sundstrand RATs have a RAT yoke 
fitting made from aluminum material. Therefore, those airplanes are now 
subject to the same replacement requirements of AD 2007-03-09 as those 
airplanes equipped with Dowty Rotol RATs.

Relevant Service Information

    Airbus has issued Service Bulletin A310-57-2086, Revision 01, dated 
September 3, 2007 (for Model A310 series airplanes); and Service 
Bulletin A300-57-6099, Revision 01, dated September 3, 2007 (for Model 
A300-600 series airplanes). (AD 2007-03-09 refers to Airbus Service 
Bulletins A310-57-2086, dated March 1, 2005, and A300-57-6099, dated 
February 23, 2005; as applicable; as appropriate sources of service 
information for accomplishing the required replacement.) The 
replacement procedures specified in Revision 01 of the service 
bulletins are identical to that in the original issues of the service 
bulletins. No additional work is recommended for airplanes modified by 
the original issues of the service bulletins.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. EASA mandated the 
service information and issued airworthiness directive 2007-0273, dated 
October 23, 2007, to ensure the continued airworthiness of these 
airplanes in the European Union.

FAA's Determination and Requirements of the Proposed AD

    These airplanes 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. As described in FAA 
Order 8100.14A, ``Interim Procedures for Working with the European 
Community on Airworthiness Certification and Continued Airworthiness,'' 
dated August 12, 2005, EASA has kept the FAA informed of the situation 
described above. We have examined EASA'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 2007-03-09. This proposed AD 
would continue to require replacing the aluminum yoke fitting of the 
swivel coupling of the RAT with a new steel yoke fitting and revising 
the FAA-approved maintenance program to include a new airplane 
maintenance manual task that specifies a detailed inspection after each 
RAT retraction. This proposed AD also would require those actions for 
additional airplanes and would revise the FAA-approved maintenance 
program to include procedures for replacing the RAT swivel coupling 
fork fitting with a new steel part only (the existing procedures allow 
replacement with either an aluminum or steel part).

Difference Between This AD and EASA Airworthiness Directive

    EASA airworthiness directive 2007-0273 applies to the following 
U.S.-registered airplanes: Airbus Model A310 and A300-600 series 
airplanes, except for airplanes on which Airbus Modification 12986 or 
19578 has been done in production or on which Airbus Service Bulletin 
A310-57-2086 or A300-57-6099 has been done. This proposed AD, as did AD 
2007-03-09, would affect all Model A300, A300-600, and A310 series 
airplanes. AD 2007-03-09 combined two French airworthiness directives 
(i.e., F-2005-089, dated June 8, 2005, and F-2005-090 R1, dated July 6, 
2005), which affect additional airplanes not identified in EASA 
airworthiness directive 2007-0273.
    Unlike EASA airworthiness directive 2007-0273, this proposed AD 
would require revising the FAA-approved maintenance program to specify 
an inspection for breaks of the bottom flange of the RAT swivel 
coupling yoke fitting after each RAT retraction; and replacement of the 
RAT swivel coupling yoke fitting with a new steel part. This action is 
necessary to ensure that only steel yoke fittings are installed.

Change to Existing AD

    This proposed AD would retain certain requirements of AD 2007-03-
09. Since AD 2007-03-09 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 2007-03-09              this  proposed AD
------------------------------------------------------------------------
Paragraph (b)...........................  Paragraph (f).
Paragraph (c)...........................  Paragraph (g).
------------------------------------------------------------------------

Costs of Compliance

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

[[Page 60205]]



                                                                     Estimated Costs
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                                                                                                                          Number of U.S.-
                         Action                             Work hours     Average labor       Parts         Cost per       registered      Fleet cost
                                                                           rate per hour                     airplane        airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Replacement.............................................              14             $80            $470          $1,590             205        $325,950
Revision of FAA-approved maintenance program............               1              80            None              80             205          16,400
--------------------------------------------------------------------------------------------------------------------------------------------------------

    In consideration of the compliance time and effective date for 
accomplishing the replacement and revision of the FAA-approved 
maintenance program required by AD 2007-03-09 (retained in paragraphs 
(f) and (g) of this proposed AD), we assume that operators of the 
affected airplanes have already initiated the required actions. The 
proposed AD would add no new costs associated with those airplanes.

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 and placed it in the AD docket. 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 39-14920 (72 FR 5157, February 5, 2007) and adding 
the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2008-1082; Directorate Identifier 2007-NM-
337-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by November 
10, 2008.

Affected ADs

    (b) This AD supersedes AD 2007-03-09.

Applicability

    (c) This AD applies to all Model A300 airplanes; Model A300 B4-
601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and 
C4-605R Variant F airplanes; and Model A310 airplanes, certificated 
in any category.

Unsafe Condition

    (d) This AD results from a report that an additional swivel 
coupling of the RAT yoke fitting was found cracked while 
accomplishing the requirements of the existing AD. We are issuing 
this AD to prevent misrigging of the ejection jack of the ram air 
turbine (RAT) and to ensure removal of any RAT yoke fitting made 
from aluminum material. Such conditions could result in a broken or 
cracked swivel coupling and consequent failure of the RAT yoke 
fitting, which could result in the loss of RAT function and possible 
loss of critical flight control systems in the event of certain 
emergency situations.

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.

Certain Requirements of AD 2007-03-09:

Replacement

    (f) For Model A300 airplanes, Model A300-600 series airplanes, 
and Model A310 airplanes equipped with Dowty Rotol RATs, except 
airplanes on which Airbus Modification 12986 has been done: Within 
12 months after March 12, 2007 (the effective date of AD 2007-03-
09), replace the RAT swivel coupling fork fitting with a new steel 
fitting, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-57-0244, dated March 4, 2005 (for Model 
A300 airplanes); A300-57-6099, dated February 23, 2005 (for Model 
A300-600 series airplanes); or A310-57-2086, dated March 1, 2005 
(for Model A310 airplanes); as applicable; except as provided by 
paragraph (h) of this AD.

Revisions of FAA-Approved Maintenance Program

    (g) For all airplanes: Within 3 months after March 12, 2007, 
incorporate the information in the applicable aircraft maintenance 
manual (AMM) specified in paragraphs (g)(1), (g)(2), and (g)(3) of 
this AD, into the FAA-approved maintenance program to specify an 
inspection for breaks of the bottom flange of the RAT swivel 
coupling yoke fitting after each RAT retraction; and replacement of 
the RAT swivel coupling yoke fitting with a new aluminum or steel 
part as applicable; in accordance with a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the Direction G[eacute]n[eacute]rale de 
l'Aviation Civile (or its delegated agent); or European Aviation 
Safety Agency (or its delegated agent). The page blocks specified in 
paragraphs (g)(1), (g)(2), and (g)(3) of this AD, as applicable, are 
one approved method for the actions required by paragraph (g) of 
this AD. Thereafter, except as provided by paragraph (l) of this AD, 
no alternative inspection intervals may be approved for the bottom 
flange of the RAT swivel coupling yoke fitting.
    (1) Airbus A300-600 AMM, Chapter 29-25-00, Page Block 301, dated 
June 1, 2005.
    (2) Airbus A310 AMM, Chapter 29-25-00, Page Block 301, dated 
June 1, 2005.

[[Page 60206]]

    (3) Airbus A300 AMM Chapter 29-25-00, Page Block 301, dated 
March 1, 2006.

    Note 1: After revising the maintenance program to include the 
required periodic inspections according to paragraph (g) or (k) of 
this AD, operators do not need to make a maintenance log entry to 
show compliance with this AD every time those inspections are 
accomplished thereafter.


    Note 2: This AD requires revisions to certain operator 
maintenance documents to include new inspections. Compliance with 
these inspections is required by 14 CFR 91.403(c). For airplanes 
that have been previously modified, altered, or repaired in the 
areas addressed by these inspections, the operator may not be able 
to accomplish the inspections described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must 
request approval for an alternative method of compliance according 
to paragraph (l) of this AD. The request should include a 
description of changes to the required inspections that will ensure 
the continued damage tolerance of the affected structure. The FAA 
has provided guidance for this determination in Advisory Circular 
(AC) 25-1529-1.

New Requirements of This AD

Revised Service Bulletins

    (h) As of the effective date of this AD, use only the 
Accomplishment Instructions of Airbus Service Bulletin A310-57-2086, 
Revision 01, dated September 3, 2007 (for Model A310 series 
airplanes); or Airbus Service Bulletin A300-57-6099, Revision 01, 
dated September 3, 2007 (for Model A300-600 series airplanes); as 
applicable; to do the replacement required by paragraph (f) of this 
AD.

Replacement

    (i) For airplanes identified in Table 1 of this AD: Before 102 
months since first flight, or within 12 months after the effective 
date of this AD, whichever occurs later, replace the aluminum yoke 
fitting of the swivel coupling of the RAT with a new steel yoke 
fitting, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A310-57-2086, Revision 01, dated September 
3, 2007 (for Model A310 series airplanes); or Airbus Service 
Bulletin A300-57-6099, Revision 01, dated September 3, 2007 (for 
Model A300-600 series airplanes); as applicable.

           Table 1--Applicability of paragraph (i) of This AD
------------------------------------------------------------------------
                                Except for those
           Model--            airplanes on which--      Or on which--
------------------------------------------------------------------------
(1) A310 series airplanes     Airbus Modification   Airbus Service
 equipped with Hamilton        12986 or 19578 has    Bulletin A310-57-
 Sundstrand RAT.               been done in          2086, dated March
                               production.           1, 2005; or
                                                     Revision 01, dated
                                                     September 3, 2007
                                                     has been done in
                                                     service.
(2) A300-600 series           Airbus Modification   Airbus Service
 airplanes equipped with       12986 or 19578 has    Bulletin A300-57-
 Hamilton Sundstrand RAT.      been done in          6099, dated
                               production.           February 23, 2005;
                                                     or Revision 01,
                                                     dated September 3,
                                                     2007; has been done
                                                     in service.
------------------------------------------------------------------------

    (j) Replacements done before the effective date of this AD in 
accordance with Airbus Service Bulletin A310-57-2086, dated March 1, 
2005 (for Model A310 series airplanes); or Airbus Service Bulletin 
A300-57-6099, dated February 23, 2005 (for Model A300-600 series 
airplane); as applicable; are acceptable for compliance with the 
requirements of paragraph (i) of this AD.

Revision of FAA-Approved Maintenance Program

    (k) For all airplanes: Within 3 months after the effective date 
of this AD, incorporate the information in the applicable AMM 
specified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD, into 
the FAA-approved maintenance program to specify an inspection for 
breaks of the bottom flange of the RAT swivel coupling yoke fitting 
after each RAT retraction; and replacement of the RAT swivel 
coupling yoke fitting with a new steel part; in accordance with a 
method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or European Aviation Safety 
Agency (or its delegated agent). The page blocks specified in 
paragraphs (k)(1), (k)(2), and (k)(3) of this AD, as applicable, 
that contain the inspection and replacement described previously are 
one approved method for the actions required by paragraph (k) of 
this AD. Thereafter, except as provided by paragraph (l) of this AD, 
no alternative inspection intervals may be approved for the bottom 
flange of the RAT swivel coupling yoke fitting. Accomplishing this 
incorporation terminates the requirements of paragraph (g) of this 
AD.
    (1) Airbus A300-600 AMM, Chapter 29-25-00, Page Block 301.
    (2) Airbus A310 AMM, Chapter 29-25-00, Page Block 301.
    (3) Airbus A300 AMM Chapter 29-25-00, Page Block 301.

Alternative Methods of Compliance (AMOCs)

    (l) The Manager, International Branch, ANM-116, 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: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
Washington 98057-3356; telephone (425) 227-1138; 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.

Related Information

    (m) European Aviation Safety Agency (EASA) airworthiness 
directive 2007-0273, dated October 23, 2007, and French 
airworthiness directive F-2005-089, dated June 8, 2005, also address 
the subject of this AD.

    Issued in Renton, Washington, on October 2, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-24151 Filed 10-9-08; 8:45 am]
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