[Federal Register Volume 60, Number 114 (Wednesday, June 14, 1995)]
[Rules and Regulations]
[Pages 31230-31232]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-14315]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-63-AD; Amendment 39-9272; AD 95-12-20]


Airworthiness Directives; Airbus Model A330 and 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 A330 and A340 series airplanes. This 
action requires a one-time inspection to determine the torque value of 
all wing slat track stop pins, and correction of discrepancies. This 
amendment is prompted by a report of a fuel leak that was caused by an 
incorrectly torqued slat track stop pin that punctured the slat 
canister. The actions specified in this AD are intended to prevent such 
fuel leakage conditions, which could result in inadequate fuel for 
completing a flight and could pose a fire hazard.

DATES: Effective June 29, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 29, 1995.
    Comments for inclusion in the Rules Docket must be received on or 
before August 14, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-63-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: 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: 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 A330 and A340 series airplanes. The DGAC advises that, during 
preflight refueling of a Model A340-300 airplane, a fuel leak was 
discovered in slat canister number 11 on the left wing of the airplane. 
Closer inspection revealed that the two parts of the slat track stop 
pin assembly at the end of the slat track had become loose and had 
separated from each other. This caused the length of the pin to 
increase by more than the width of the canister, thus puncturing the 
side of the slat canister close to the front of the spar attachment 
flange. The stop pin was found to be bent and detached from the slat 
track.
    A subsequent visual inspection of the pins at the other slat track 
positions on both the left and right wings of the incident airplane 
revealed excess lateral movement. A certain amount of lateral movement 
of the pins in the slat track is normal (0.2 mm to 0.3 mm, or 0.0079 
inch to 0.0118 inch). However, the pins that were inspected indicated 
lateral movement up to 12 mm (0.472 inch). A torque check of the pins 
revealed zero torque. No additional damage to the slat canister was 
found.
    The slat track stop pin assembly consists of two parts (male and 
female), which are installed at the end of each of the slat tracks. 
Their purpose is to provide a positive stop in case of over-extension 
of the slats. The torque loading applied during installation of this 
two-part assembly provides the primary locking feature; a five-point 
internal circlip ring provides a secondary locking feature. Incorrect 
installation of these items may have contributed to the pins coming 
loose on the incident airplane. The installation procedure was 
corrected on all airplanes delivered after June 15, 1994.
    Excessive lateral movement of the stop pins can result in damage to 
the slat canister during extension or retraction of the slats. 
Excessive damage to the canister could lead to a running 

[[Page 31231]]
fuel leak. Such a fuel leak could result in inadequate fuel for 
completing a flight and could pose a fire hazard.
    Airbus Industrie has issued All Operators Telex (AOT) 57-08, 
Revision 1, dated June 28, 1994, which describes procedures for a one-
time torque check of all wing slat track stop pins (32 positions), and 
retorquing, as necessary. The AOT also describes procedures for 
conducting a borescope inspection for signs of damage or wear in 
situations where more than five complete turns of the pin are needed to 
reach the required torque value. The AOT contains procedures for an 
alternative inspection procedure in which the more critically 
positioned pins are inspected initially, and the remainder of the pins 
are inspected no later than the airplane's next scheduled ``C'' check. 
The DGAC classified this service bulletin as mandatory and issued 
French airworthiness directives 97-146-003(B) (applicable to Model A330 
series airplanes) and 94-147-009(B) (applicable to Model A340 series 
airplanes), both dated July 6, 1994, 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 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, this AD is 
being issued to prevent fuel leakage caused by incorrectly torqued slat 
track stop pins puncturing the slat canister. This condition could 
result in inadequate fuel for completing a flight and could pose a fire 
hazard. This AD requires a one-time torque check of all wing slat track 
stop pins, and retorquing, as necessary. It also requires a borescope 
inspection for signs of damage or wear in situations where more than 
five complete turns of the pin are needed to reach the required torque 
value. The AD provides for an alternative inspection procedure in which 
inspection of the pins is conducted in two stages. The actions are 
required to be accomplished in accordance with the service bulletin 
described previously.
    There currently are no affected Model A330 or A340 series airplanes 
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, it would require approximately 20 work hours to 
accomplish the required actions, at an average labor charge of $60 per 
work hour. Based on these figures, the total cost impact of this AD 
would be $1,200 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-63-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. 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:

95-12-20  Airbus Industrie: Amendment 39-9272. Docket 95-NM-63-AD.

    Applicability: Model A330-301 series airplanes that were 
delivered prior to June 

[[Page 31232]]
15, 1994; and Model A340-211, -311, -212, and -312 series airplanes 
that were delivered prior to June 15, 1994; 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 (c) 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 fuel leaks caused by an incorrectly torqued slat 
track stop puncturing the slat canister, which can result in 
inadequate fuel for completing a flight and can pose a fire hazard, 
accomplish the following:
    (a) Except as provided by paragraph (b) of this AD: Within 10 
days after the effective date of this AD, perform an inspection to 
determine the torque value of all wing slat track stop pins (32 
positions), in accordance with Airbus All Operators Telex (AOT) 57-
08, Revision 1, dated June 28, 1994.
    (1) If the torque value of all wing slat track stop pins is 
within the acceptable range specified in the AOT, no further action 
is required by this AD.
    (2) If any slat track stop pin is loose, or there is excessive 
axial movement (in excess of 0.3 mm or 0.118 inch), prior to further 
flight, retorque the pin in accordance with the AOT.
    (3) If a slat track stop pin is loose, and requires more than 
five complete turns of the pin to reach the required torque value, 
prior to further flight, perform a borescope inspection to detect 
damage or wear of the internal sides of the slat canisters, in 
accordance with the AOT.
    (i) If the borescope inspection reveals no signs of damage or 
wear, no further action is required by this AD.
    (ii) If the borescope inspection reveals evidence of damage or 
wear, but the canister is not perforated, repair the canister in 
accordance with paragraph 4.1.3(B) of the AOT within 450 flight 
cycles after the borescope inspection.
    (iii) If the borescope inspection reveals that the canister is 
perforated, prior to further flight, either repair in accordance 
with PMS 01-04-02 or replace the canister in accordance with the 
AOT.
    (b) As an alternative to the requirements of paragraph (a) of 
this AD, operators may accomplish the following: Within 10 days 
after the effective date of this AD, perform an inspection to 
determine the torque value of the slat track stop pins at positions 
4, 5, 10, and 11 (immediately inboard and outboard of the pylons), 
in accordance with Airbus AOT 57-08, Revision 1, dated June 28, 
1994.
    (1) If the torque value of each of the slat track stop pins at 
positions 4, 5, 10, and 11 is found to be is within the acceptable 
range specified in the AOT, within 450 flight cycles, perform an 
inspection to determine the torque value of the remainder of the 
slat track stop pins on both wings, in accordance with the AOT.
    (2) If any of the slat track stop pins at positions 4, 5, 10, 
and 11 is found to be loose, prior to further flight, perform an 
inspection to determine the torque value of the remainder of the 
slat track stop pins on both wings, in accordance with the AOT.
    (3) If any slat track stop pin is found to be loose during any 
inspection required by this paragraph, or if there is excessive 
axial movement (in excess of 0.3 mm or 0.118 inch), prior to further 
flight, retorque the pin in accordance with the AOT.
    (4) If any slat track stop pin is loose during any inspection 
required by this paragraph, and requires more than five complete 
turns of the pin to reach the required torque value, prior to 
further flight, perform a borescope inspection to detect damage or 
wear of the internal sides of the slat canisters, in accordance with 
the AOT.
    (i) If the borescope inspection reveals no signs of damage or 
wear, no further action is required by this AD.
    (ii) If the borescope inspection reveals evidence of damage or 
wear, but the canister is not perforated, repair the canister in 
accordance with paragraph 4.1.3(B) of the AOT within 450 flight 
cycles after the borescope inspection.
    (iii) If the borescope inspection reveals that the canister is 
perforated, prior to further flight, either repair in accordance 
with PMS 01-04-02, or replace the canister in accordance with the 
AOT.
    (c) 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.

    (d) 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.
    (e) The inspections, retorquing procedures, and replacement 
actions shall be done in accordance with Airbus All Operators Telex 
57-08, Revision 1, dated June 28, 1994. 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.
    (f) This amendment becomes effective on June 29, 1995.

    Issued in Renton, Washington, on June 6, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-14315 Filed 6-13-95; 8:45 am]
BILLING CODE 4910-13-U