AD Amdt-39-9220

[Federal Register Volume 60, Number 92 (Friday, May 12, 1995)]
[Rules and Regulations]
[Pages 25604-25606]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 95-10986]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93-NM-56-AD; Amendment 39-9220; AD 95-10-03]


Airworthiness Directives; Airbus Industrie Model A300, A300-600, 
and A310 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Industrie Model A300, A300-600, and A310 
series airplanes, that requires inspections to detect cracks in the 
lower spar axis of the pylon between ribs 9 and 10, and repair, if 
necessary. This amendment is prompted by a report indicating that 
fatigue cracks have been found on the lower spar of the pylon. The 
actions specified by this AD are intended to prevent such fatigue 
cracking, which could result in reduced structural integrity of the 
lower spar of the pylon.

DATES: Effective June 12, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 12, 1995.

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Stephen Slotte, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2797; fax (206) 227-1320.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Airbus Industrie Model 
A300, A300-600, and A310 series airplanes was published in the Federal 
Register on December 6, 1993 (58 FR 64200). That action proposed to 
require repetitive internal eddy current inspections to detect cracks 
in the lower spar axis of the pylon between ribs 9 and 10, and repair, 
if necessary.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    Both commenters support the proposed rule.
    Since the issuance of the proposed rule, Airbus Industrie issued 
Revision 1, dated October 15, 1993, of the service bulletins cited in 
the proposal: Service Bulletin No.'s A300-54-071 (for Model A300 series 
airplanes), A300-54-6011 (for Model A300-600 series airplanes), and 
A310-54-2016 (for Model A310 series airplanes). Revision 1 of these 
service bulletins incorporates certain kit and technical information 
and revises the work hour estimate associated with repair of the lower 
spar. The FAA has revised the final rule to reference these latest 
service bulletin revisions as additional sources of service information 
for accomplishment of certain actions required by this AD. In addition, 
the FAA has revised the applicability of the final rule to specify that 
the AD applies to those airplanes listed in Revision 1 of the service 
bulletins. (This change adds no new airplanes to those specified 
originally in the applicability of the proposed rule.)
    The service bulletin citation contained in paragraph (b) of the 
final rule has been revised to correct a typographical error. The 
correct date of the original issue of Airbus Industrie Service Bulletin 
No. A300-54-6011 is November 12, 1991 (rather than November 12, 1992, 
as indicated in the proposal).
    Since the issuance of the proposed rule, Airbus Industrie also has 
issued Service Bulletins A300-54-0079 (for Model A300 series 
airplanes); A300-54-6019 (for Model A300-600 series airplanes); and 
A310-54-2022 (for Model A310 series airplanes); all dated October 15, 
1993. These service bulletins describe procedures for modification of 
the lower spar between ribs 9 and 10. This modification involves 
installation of an outer doubler on the undamaged structure of the 
lower spars between ribs 9 and 10. For Model A300 and A310 series 
airplanes, accomplishment of the modification eliminates the need for 
the internal eddy current inspections specified in the Airbus service 
bulletins previously described (and proposed in the notice). For Model 
A300-600 series airplanes, accomplishment of the modification reduces 
the probability of cracking in the lower spar of the pylon and, 
thereby, allows an extension of the initial inspection threshold and 
interval for accomplishing the internal eddy current inspections. The 
Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, issued French airworthiness 
directive 92-049-130(B)R2, dated March 2, 1994, to reference these 
service bulletins.
    Accordingly, the FAA has revised this final rule to provide 
operators with the option of accomplishing the modification of the 
lower spar as terminating action for the repetitive eddy current 
inspections of Model A300 and A310 series airplanes. The FAA also has 
revised this final rule to extend the inspection threshold and 
repetitive inspection intervals of Model A300-600 series airplanes on 
which the modification of the lower spar is accomplished.
    Additionally, the FAA revised the economic impact information, 
below, to specify the costs associated with modifying the lower spar, 
should an operator elect to do so. Further, the FAA has recently 
reviewed the figures it has used over the past several years in 
calculating the economic impact of AD activity. In order to account for 
various inflationary costs in the airline industry, the FAA has 
determined that it is necessary to increase the labor rate used in 
these calculations from $55 per work hour to $60 per work hour. The 
economic impact information, below, has been revised to reflect this 
increase in the specified hourly labor rate.
    Subsequent to the issuance of the notice, the FAA discovered that 
reference to Model A300 B2-203 series airplanes was omitted 
inadvertently from paragraph (a) of the proposed rule. This airplane 
model is not operated [[Page 25605]] currently by U.S. operators and, 
therefore, is not affected directly by this AD action. However, the FAA 
considers that revising paragraph (a) of the rule to include Model A300 
B2-203 series airplanes is necessary to ensure that the unsafe 
condition is addressed in the event that any of these subject airplanes 
are imported and placed on the U.S. Register in the future.
    As a result of recent communications with the Air Transport 
Association (ATA) of America, the FAA has learned that, in general, 
some operators may misunderstand the legal effect of AD's on airplanes 
that are identified in the applicability provision of the AD, but that 
have been altered or repaired in the area addressed by the AD. The FAA 
points out that all airplanes identified in the applicability provision 
of an AD are legally subject to the AD. If an airplane has been altered 
or repaired in the affected area in such a way as to affect compliance 
with the AD, the owner or operator is required to obtain FAA approval 
for an alternative method of compliance with the AD, in accordance with 
the paragraph of each AD that provides for such approvals. A note has 
been added to this final rule to clarify this long-standing 
requirement.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.
    The FAA estimates that 57 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 4 work hours per 
airplane to accomplish the required actions, and that the average labor 
rate is $60 per work hour. Based on these figures, the total cost 
impact of the AD on U.S. operators is estimated to be $13,680, or $240 
per airplane.
    The total cost impact figure discussed above is based on 
assumptions that no operator has yet accomplished any of the 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.
    Should an operator elect to accomplish the optional terminating 
action that would be provided by this AD action, it will take 
approximately 104 work hours to accomplish it, at an average labor rate 
of $60 per work hour. The cost of required parts will be approximately 
$1,500 per airplane. Based on these figures, the total cost impact of 
the optional terminating action is estimated to be $7,740 per airplane.
    The regulations adopted herein will not have substantial direct 
effects 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. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

95-10-03  Airbus Industrie: Amendment 39-9220. Docket 93-NM-56-AD.

    Applicability: Model A300, A300-600, and A310 series airplanes; 
as listed in Revision 1 of Airbus Industrie Service Bulletin No.'s 
A300-54-071, A300-54-6011, and A310-54-2016, all dated October 15, 
1993; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must use the authority 
provided in paragraph (d) to request approval from the FAA. This 
approval may address either no action, if the current configuration 
eliminates the unsafe condition; or different actions necessary to 
address the unsafe condition described in this AD. Such a request 
should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent reduced structural integrity of the lower spar of the 
pylon, accomplish the following:
    (a) For Model A300 B4-2C, B2K-3C, B2-203, B4-103, and B4-203 
series airplanes: Prior to the accumulation of 9,000 total landings, 
or within 500 landings after the effective date of this AD, 
whichever occurs later, perform an internal eddy current inspection 
to detect cracks in the lower spar axis of the pylon between ribs 9 
and 10, in accordance with Airbus Industrie Service Bulletin No. 
A300-54-071, dated November 12, 1991; or Revision 1, dated October 
15, 1993.
    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 2,500 landings.
    (2) If any crack is found that is less than or equal to 30 mm: 
Perform subsequent inspections and repair in accordance with the 
methods and times specified in the service bulletin.
    (3) If any crack is found that is greater than 30 mm, but less 
than 100 mm: Prior to the accumulation of 250 landings after crack 
discovery, repair in accordance with a method approved by the 
Manager, Standardization Branch, ANM-113, FAA, Transport Airplane 
Directorate.
    (4) If any crack is found that is greater than or equal to 100 
mm: Prior to further flight, repair in accordance with a method 
approved by the Manager, Standardization Branch, ANM-113.
    (5) Accomplishment of the modification specified in Airbus 
Industrie Service Bulletin No. A300-54-0079, dated October 15, 1993, 
constitutes terminating action for the inspections required by 
paragraph (a) of this AD.
    (b) For Model A300-600 B4-620, C4-620, -622R, and -622 series 
airplanes: Except as provided by paragraph (b)(5) of this AD, prior 
to the accumulation of 4,000 total landings, or within 500 landings 
after the effective date of this AD, whichever occurs later, perform 
an internal eddy current inspection to detect cracks in the lower 
spar axis of the pylon between ribs 9 and 10, in accordance with 
Airbus Industrie Service Bulletin No. A300-54-6011, dated November 
12, 1991, as amended by Service Bulletin Change Notice O.A., dated 
July 10, 1992; or Revision 1, dated October 15, 1993.
    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 2,500 landings. [[Page 25606]] 
    (2) If any crack is found that is less than or equal to 30 mm: 
Perform subsequent inspections and repair in accordance with the 
methods and times specified in the service bulletin.
    (3) If any crack is found that is greater than 30 mm, but less 
than 100 mm: Prior to the accumulation of 250 landings after crack 
discovery, repair in accordance with a method approved by the 
Manager, Standardization Branch, ANM-113.
    (4) If any crack is found that is greater than or equal to 100 
mm: Prior to further flight, repair in accordance with a method 
approved by the Manager, Standardization Branch, ANM-113.
    (5) Accomplishment of the modification specified in Airbus 
Industrie Service Bulletin No. A300-54-6019, dated October 15, 1993, 
increases the threshold and repetitive interval of the inspections 
required by paragraph (b) of this AD to the threshold and interval 
specified in paragraph 2.D. of the Accomplishment Instructions of 
Airbus Industrie Service Bulletin No. A300-54-6011, Revision 1, 
dated October 15, 1993.
    (c) For Model A310-221, -222, -322, -324, and -325 series 
airplanes: Prior to the accumulation of 25,000 total landings, or 
within 500 landings after the effective date of this AD, whichever 
occurs later, perform an internal eddy current inspection to detect 
cracks in the lower spar axis of the pylon between ribs 9 and 10, in 
accordance with Airbus Industrie Service Bulletin No. A310-54-2016, 
dated November 12, 1991; or Revision 1, dated October 15, 1993.
    (1) If no crack is found, repeat the inspection thereafter at 
intervals not to exceed 2,500 landings.
    (2) If any crack is found that is less than or equal to 30 mm: 
Perform subsequent inspections and repair in accordance with the 
methods and times specified in the service bulletin.
    (3) If any crack is found that is greater than 30 mm, but less 
than 100 mm: Prior to the accumulation of 250 landings after crack 
discovery, repair in a accordance with a method approved by the 
Manager, Standardization Branch, ANM-113.
    (4) If any crack is found that is greater than or equal to 100 
mm: Prior to further flight, repair in accordance with a method 
approved by the Manager, Standardization Branch, ANM-113.
    (5) Accomplishment of the modification specified in Airbus 
Industrie Service Bulletin No. A310-54-2022, dated October 15, 1993, 
constitutes terminating action for the inspections required by 
paragraph (c) of this AD.
    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Standardization Branch, ANM-113. 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Standardization Branch, ANM-113.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (e) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the airplane to a location where the 
requirements of this AD can be accomplished.
    (f) The actions shall be done in accordance with the following 
Airbus Industrie service bulletins, as applicable, which contain the 
specified effective pages:

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                                                                 Revision level shown on                        
 Service bulletin referenced and date           Page No.                   page             Date shown on page  
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A300-54-071, November 12, 1991........  1-19...................  Original...............  November 12, 1991.    
A300-54-071, Revision 1, October 15,    1-20...................  1......................  October 15, 1993.     
 1993.                                                                                                          
A300-54-0079, October 15, 1993........  1-16...................  Original...............  October 15, 1993.     
A300-54-6011, November 12, 1991.......  1-17...................  Original...............  November 12, 1991.    
Service Bulletin Change Notice O.A.,    (This document is not    Original...............  July 10, 1992.        
 A300-54-6011, July 10, 1992.            numbered).                                                             
A300-54-6011, Revision 1, October 15,   1-10, 12-19............  1......................  October 15, 1993.     
 1993.                                                                                                          
                                        11.....................  Original...............  November 12, 1991.    
A300-54-6019, October 15, 1993........  1-11...................  Original...............  October 15, 1993.     
A310-54-2016, November 12, 1991.......  1-17...................  Original...............  November 12, 1991.    
A310-54-2016, Revision 1, October 15,   1-10, 12, 17...........  1......................  October 15, 1993.     
 1993.                                                                                                          
                                        11, 13-16..............  Original...............  November 12, 1991.    
A310-54-2022, October 15, 1993........  1-11...................  Original...............  October 15, 1993.     
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    This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the Office of the Federal Register, 800 North Capitol 
Street, NW., suite 700, Washington, DC.
    (g) This amendment becomes effective on June 12, 1995.

    Issued in Renton, Washington, on April 28, 1995.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-10986 Filed 5-11-95; 8:45 am]
BILLING CODE 4910-13-U