[Federal Register Volume 61, Number 37 (Friday, February 23, 1996)]
[Rules and Regulations]
[Pages 6924-6927]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-3149]



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[[Page 6925]]



DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-262-AD; Amendment 39-9515; AD 96-04-04]


Airworthiness Directives; Airbus Model A340 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A340 series airplanes. This action 
requires repetitive inspections to detect corrosion and cracking of the 
shortening mechanism pins in the main landing gear (MLG), and repair or 
replacement, if necessary. It also requires replacement of the 
shortening mechanism pin and retraction mechanism pins; the forward 
pintle pin; the shortening mechanism bellcrank pin; and the bellcrank 
subassembly of the shortening mechanism. This amendment is prompted by 
reports of failure of the shortening mechanism pins due to improper 
grinding of the chrome plating during manufacture, which led to the 
initiation of stress corrosion and cracks. The actions specified in 
this AD are intended to prevent failure of these pins, which could lead 
to a significant reduction of the shock absorber capability or damage 
to various components of the MLG, and eventually could lead to the 
failure of the MLG.

DATES: Effective March 11, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 11, 1996.
    Comments for inclusion in the Rules Docket must be received on or 
before April 23, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-262-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    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 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.

FOR FURTHER INFORMATION CONTACT: Charles Huber, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2589; fax (206) 227-1149.

SUPPLEMENTARY INFORMATION: The Direction Generale de l'Aviation Civile 
(DGAC), which is the airworthiness authority for France, recently 
notified the FAA that an unsafe condition may exist on certain Airbus 
Model A340 series airplanes. The DGAC advises that there have been two 
cases of failure of the shortening mechanism pin of the main landing 
gear (MLG) assembly on in-service airplanes.
    In one case, investigation revealed that the pin had broken into 
three parts, the chrome plating was detached from the base metal around 
the breaks, and heavy corrosion was present on all of the fracture 
surfaces. A metallurgical analysis of the broken pin concluded that the 
pin fractures were the result of cracks in the pin's chrome plating and 
subsequent stress corrosion. The cracks in the chrome plating most 
likely occurred as a result of ``grinding abuse'' when the pin was 
ground during manufacture. The subsequent penetration of moisture 
through the cracks to the base metal initiated the stress corrosion and 
the local detachment of the chrome plating.
    In the second case, investigation revealed that the pin had failed 
as a result of damage caused by stress corrosion.
    The DGAC also advises that similar ``grinding abuse'' may also be 
present on some forward pintle pins installed on the main strut and 
dressings of certain affected airplanes, and on the shortening 
mechanism bellcrank pins of the bellcrank subassembly of the MLG.
    Failure of the shortening mechanism pin on the MLG could result in 
substantial damage to the shortening mechanism, the shock absorber, and 
the inner top side of the main fitting. This condition could lead to a 
significant reduction of the shock absorber capability, and eventually 
could lead to the failure of the MLG.
    Likewise, failure of the forward pintle pins or the shortening 
mechanism bellcrank pins could also result in damage to the shortening 
mechanism and/or the surrounding area and components, and eventually 
could lead to the failure of the MLG.
    Airbus Industrie has issued the following service bulletins that 
contain procedures to address this problem:
    1. Airbus Service Bulletin A340-32-4050, dated April 10, 1995; and 
Revision 1, dated May 17, 1995. These service bulletins describe 
procedures for conducting repetitive visual inspections to detect 
cracks and corrosion of the shortening mechanism pins. The inspection 
procedures also call for a one-time lubricating of the affected 
shortening mechanism links. The service bulletins also describe 
procedures for replacement of the shortening mechanism pin and 
retraction mechanism pins of the MLG (left- and right-hand side) with 
pins that are properly chrome-plated and not susceptible to problems 
associated with corrosion. (These service bulletins refer to Messier-
Dowty Service Bulletins A33/34-32-29 and A33/34-32-30 for more detailed 
procedural instructions.)
    2. Airbus Service Bulletin A340-32-4058, dated April 10, 1995; and 
Revision 1, dated May 17, 1995. These service bulletins describe 
procedures for removing discrepant forward pintle pins and replacing 
them with new or reworked pintle pins that are not susceptible to the 
problems associated with corrosion. This replacement will ensure the 
integrity of the affected components of the MLG. (These service 
bulletins refer to Messier-Dowty Service Bulletins A33/34-32-28 and 
A33/34-32-32 for more detailed procedural instructions.)
    3. Airbus Service Bulletin A340-32-4062, dated May 17, 1995. This 
service bulletin describes procedures for replacing discrepant 
shortening mechanism bellcrank pins with new or serviceable pins that 
are not susceptible to the problems associated with corrosion. It also 
describes procedures for replacing the bellcrank subassembly of the 
shortening mechanism of the MLG. These replacements will ensure the 
integrity of the affected components of the bellcrank and the MLG. 
(This service bulletin refers to Messier-Dowty Service Bulletins A33-
34-32-44 and A33/34-32-45 for more detailed procedural instructions.
    The DGAC classified these service bulletins as mandatory and issued 
French airworthiness directive (CN) 94-244-012(B)R3, dated July 19, 
1995, in order to assure the continued airworthiness of these airplanes 
in France.
    This airplane model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.19) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the DGAC, reviewed all available information, and determined that AD 
action is necessary for products of this 

[[Page 6926]]
type design that are certificated for operation in the United States.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, this AD is being issued to prevent failure of the 
MLG. This AD requires, initially, repetitive visual inspections to 
detect damage or cracks of the shortening mechanism pivot pin, and 
replacement, if necessary. It also requires a one-time lubrication 
(greasing) of the MLG shortening mechanism main links.
    This AD also requires replacement of the following items:
    1. The shortening mechanism pivot pin, and the retraction mechanism 
pins of the MLG on the left- and right-hand sides (after these 
replacements are accomplished, the required repetitive visual 
inspections are terminated);
    2. The forward pintle pin fitted to the MLG;
    3. The shortening mechanism bellcrank pin of the MLG; and
    4. The bellcrank subassembly of the shortening mechanism of the 
MLG.
    These actions are required to be accomplished in accordance with 
the service bulletins described previously.
    None of the Model A340 series airplanes affected by this action are 
on the U.S. Register. All airplanes included in the applicability of 
this rule currently are operated by non-U.S. operators under foreign 
registry; therefore, they are not directly affected by this AD action. 
However, the FAA considers that this rule 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.
    Should an affected airplane be imported and placed on the U.S. 
Register in the future, the following costs could be expected:
    Inspection of the shortening mechanism pivot pin would require 
approximately .5 work hour to accomplish the required actions, at an 
average labor charge of $60 per work hour. Based on these figures, the 
cost impact of this inspection requirement would be $30 per airplane 
per inspection cycle.
    Replacement of the shortening mechanism pivot pin and retraction 
mechanism pins would require approximately 118 work hours per airplane 
to accomplish, at an average labor charge of $60 per work hour. Based 
on these figures, the cost impact of this replacement requirement would 
be $7,080 per airplane.
    Replacement of the forward pintle pin would require approximately 
92 work hours per airplane to accomplish, at an average labor charge of 
$60 per work hour. Based on these figures, the cost impact of this 
replacement requirement would be $5,520 per airplane.
    Replacement of the shortening mechanism bellcrank pin and bellcrank 
subassembly would require approximately 13 work hours per airplane to 
accomplish, at an average labor charge of $60 per work hour. Based on 
these figures, the cost impact of this replacement requirement would be 
$780 per airplane.
    Since this AD action does not affect any airplane that is currently 
on the U.S. register, it has no adverse economic impact and imposes no 
additional burden on any person. Therefore, notice and public 
procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and opportunity for public comment, comments are 
invited on this rule. Interested persons are invited to comment on this 
rule by submitting such written data, views, or arguments as they may 
desire. Communications shall identify the Rules Docket number and be 
submitted in triplicate to the address specified under the caption 
ADDRESSES.
    All communications received on or before the closing date for 
comments will be considered, and this rule may be amended in light of 
the comments received. Factual information that supports the 
commenter's ideas and suggestions is extremely helpful in evaluating 
the effectiveness of the AD action and determining whether additional 
rulemaking action would be needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 95-NM-262-AD.'' The postcard will be date stamped and 
returned to the commenter.
    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. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

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

96-04-04  Airbus: Amendment 39-9515. Docket 95-NM-262-AD.

    Applicability: Model A340 series airplanes; having 
manufacturer's serial numbers (MSN) 002 through 009 inclusive, 011, 
013 through 016 inclusive, 018 through 029 inclusive, 031 through 
036 inclusive, or 038; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
otherwise 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 

[[Page 6927]]
owner/operator must request approval for an alternative method of 
compliance in accordance with paragraph (d) of this AD. The request 
should include an assessment of the effect of the modification, 
alteration, or repair on the unsafe condition addressed by this AD; 
and, if the unsafe condition has not been eliminated, the request 
should include specific proposed actions to address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent collapse of the main landing gear, accomplish the 
following:
    (a) For airplanes having MSN 005 through 009 inclusive, 011, 013 
through 016 inclusive, 018 through 029 inclusive, 031 through 034 
inclusive, or 038: Accomplish the requirements of paragraphs (a)(1) 
and (a)(2) of this AD:
    (1) Within 7 days after the effective date of this AD, perform a 
visual inspection to detect corrosion and cracks of the shortening 
mechanism (pivot) pins of the main landing gear (MLG), in accordance 
with Airbus Service Bulletin A340-32-4050, dated April 10, 1995, or 
Revision 1, dated May 17, 1995.
    (i) If no corrosion or cracking is found, repeat the inspection 
thereafter at intervals not to exceed 7 days.
    (ii) If any corrosion or cracking is found, prior to further 
flight, replace the shortening mechanism pin and the retraction 
mechanism pin with a new pin in accordance with the service 
bulletin. Accomplishment of this replacement constitutes terminating 
action for the repetitive inspections required by paragraph 
(a)(1)(i) of this AD.
    (2) Within 7 days after the effective date of this AD, perform a 
one-time lubrication (greasing) of the MLG shortening mechanism main 
links in accordance with the service bulletin.
    (b) Prior to the accumulation of 1,500 total landings, or within 
3 months after the effective date of this AD, whichever occurs 
later, but no later than 12 months after the effective date of this 
AD, accomplish the requirements of paragraphs (b)(1), (b)(2), and 
(b)(3) of this AD, as applicable.
    (1) For airplanes having MSN 005 through 009 inclusive, 011, 013 
through 016 inclusive, 018 through 029 inclusive, 031 through 034 
inclusive, or 038: Replace the shortening mechanism pivot pin, and 
the retraction mechanism pins of the MLG, left- and right-hand side, 
in accordance with Airbus Service Bulletin A340-32-4050, dated April 
10, 1995, or Revision 1, dated May 17, 1995.
    (2) For airplanes having MSN 021 through 029 inclusive, or 031 
through 034 inclusive: Replace the forward pintle pins fitted to the 
MLG in accordance with Airbus Service Bulletin A340-32-4058, dated 
April 10, 1995, or Revision 1, dated May 17, 1995.
    (3) For airplanes having MSN 002 through 009 inclusive, 011, 013 
through 016 inclusive, 018 through 029 inclusive, or 031 through 036 
inclusive: Replace the shortening mechanism bellcrank pin of the MLG 
in accordance with Airbus Service Bulletin A340-32-4062, dated May 
17, 1995.
    (c) For airplanes having MSN 002 through 009 inclusive, 011, 013 
through 016 inclusive, 018 through 029 inclusive, or 031 through 036 
inclusive: Prior to the accumulation of 7,250 total landings, or 
within 3 months after the effective date of this AD, whichever 
occurs later, replace the bellcrank subassembly of the shortening 
mechanism of the MLG in accordance with Airbus Service Bulletin 
A340-32-4062, dated May 17, 1995.
    (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, 
FAA, Transport Airplane Directorate. 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 
sections 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 service bulletins, which contain the following list of 
effective pages:

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         Airbus service bulletin and date                        Page No.               Revision level shown on page          Date shown on page        
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A340-32-4050, April 10, 1995.....................  1-15-                                (Original)-                   April 10, 1995.                   
A340-32-4050, Revision 1, May 17, 1995-..........  1, 2, 5, 10-                         1-                            May 17, 1995.                     
                                                   3, 4, 6-9, 11-15-                    (Original)-                   April 10, 1995.                   
A340-32-4058, April 10, 1995.....................  1-10-                                (Original)-                   April 10, 1995.                   
A340-32-4058, Revision 1, May 17, 1995-..........  1-3, 7-9-                            1-                            May 17, 1995.                     
                                                   4-6, 10-                             (Original)-                   April 10, 1995.                   
A340-32-4062, May 17, 1995.......................  1-10-                                (Original)-                   May 17, 1995.                     
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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 March 11, 1996.

    Issued in Renton, Washington, on February 7, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-3149 Filed 2-22-96; 8:45 am]
BILLING CODE 4910-13-P