AD 2001-08-12

[Federal Register Volume 66, Number 81 (Thursday, April 26, 2001)]
[Rules and Regulations]
[Pages 20907-20910]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-9878]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-180-AD; Amendment 39-12189; AD 2001-08-12]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A340 Series Airplanes 
Equipped With CFM International CFM56-5C Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Model A340 series airplanes. This action 
requires repetitive inspections of the pivoting door roller fittings of 
the upper and lower thrust reversers for cracks, and corrective action, 
if necessary. This action is prompted by issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. This action is intended to detect and correct cracking of 
the pivoting door roller fittings of the thrust reversers, which could 
result in failure of the primary locking mechanism of the thrust 
reversers during flight, leading to reduced controllability of the 
airplane. This action is intended to address the identified unsafe 
condition.

DATES: Effective May 11, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 11, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before May 29, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-180-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
<a href="/cdn-cgi/l/email-protection#4b72662a252666222a39282426262e253f0b2d2a2a652c243d"><span class="__cf_email__" data-cfemail="b28b9fd3dcdf9fdbd3c0d1dddfdfd7dcc6f2d4d3d39cd5ddc4">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2000-NM-180-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must

[[Page 20908]]

be formatted in Microsoft Word 97 for Windows or ASCII text.
    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: Gary Lium, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1112; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The Direction Generale de l'Aviation Civile 
(DGAC), which is the airworthiness authority for France, notified the 
FAA that an unsafe condition may exist on certain Airbus A340 series 
airplanes. The DGAC advises that two pilots experienced ``rev unlock'' 
warnings during flight, indicating that the thrust reversers were 
unlocked. In each incident, the warning led the pilot to turn back to 
the departure point. These warnings resulted from failure of the upper 
pivoting door roller fittings. Both fittings have been recovered and 
the failure has been confirmed to be due to fatigue. This action is 
intended to detect and correct cracking of the pivoting door roller 
fittings of the thrust reversers, which could result in failure of the 
primary locking mechanism of the thrust reversers during flight, 
leading to reduced controllability of the airplane.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A340-78-4017, dated October 14, 
1999, which describes procedures for a special detailed inspection for 
cracks in the pivoting door roller fittings of the thrust reversers. 
The inspection may be done using either an eddy current or fluorescent 
penetrant procedure.
    If cracked fittings are detected by the inspection, one must take 
one of the following actions:
    1. Replace the cracked fittings with new fittings and re-inspect 
all four fittings every 500 flight hours, or
    2. Replace all 4 fittings with new fittings, which resets the 
repetitive inspection interval to every 7,000 flight hours or 1,200 
flight cycles.
    One may also elect to replace all 4 fittings with new fittings 
without performing any inspection for cracks, which also resets the 
repetitive inspection interval to every 7,000 flight hours or 1,200 
flight cycles.
    The DGAC classified this service bulletin as mandatory and issued 
French airworthiness directive 1998-543-105(B) R2, dated November 17, 
1999, in order to assure the continued airworthiness of these airplanes 
in France.
    Airbus Service Bulletin A320-78-4017 references ROHR Alert Service 
Bulletin RA340A78-57, Revision 1, dated May 18, 1999, as an additional 
source of service information for accomplishment of the special 
detailed inspection and replacement of the pivoting door roller 
fittings on the thrust reversers.

FAA's Conclusions

    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 21.29) 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.

Explanation of Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design that may be 
registered in the United States at some time in the future, this AD is 
intended to detect and correct cracking of the pivoting door roller 
fittings on the thrust reversers, which could result in failure of the 
primary locking mechanism of the thrust reversers during flight, 
leading to reduced controllability of the airplane. This AD requires 
accomplishment of the actions specified in the Airbus service bulletin 
described previously.

Cost Impact

    None of the 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, it would require approximately 6 work hours to 
accomplish the required special detailed inspection at an average labor 
rate of $60 per work hour. Based on these figures, the cost impact of 
this AD would be $360 per airplane, per inspection cycle.

Determination of Rule's Effective Date

    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, prior 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.
    Submit comments using the following format:
    <bullet> Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    <bullet> For each issue, state what specific change to the proposed 
AD is being requested.
    <bullet> Include justification (e.g., reasons or data) for each 
request.
    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

[[Page 20909]]

submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NM-180-AD.'' The postcard will be date stamped 
and returned to the commenter.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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:

2001-08-12  Airbus Industrie: Amendment 39-12189. Docket 2000-NM-
180-AD.

    Applicability: Model A340 series airplanes, certificated in any 
category, equipped with CFM International CFM56-5C engines.

    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 request approval for an 
alternative method of compliance in accordance with paragraph (f) 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 detect and correct cracking of the pivoting door roller 
fittings on the thrust reversers, which could result in failure of 
the primary locking mechanism of the thrust reversers during flight, 
leading to reduced controllability of the airplane, accomplish the 
following:

Inspections

    (a) Except as required by paragraph (b) of this AD, perform a 
special detailed inspection of the pivoting door roller fittings for 
cracks, using the eddy current or the fluorescent penetrant 
procedure. The inspection must be performed in accordance with 
Airbus Service Bulletin A340-78-4017, dated October 14, 1999, and 
must be performed at the later of the times specified in paragraphs 
(a)(1) and (a)(2).
    (1) Prior to the accumulation of 7,000 total flight hours or 
1,200 total flight cycles, whichever occurs first; or
    (2) Within 500 flight hours after the effective date of this AD.

    Note 2: ROHR Alert Service Bulletin RA340A78-57, Revision 1, 
dated May 18, 1999, is an additional source of service information 
for accomplishment of the special detailed inspection and 
replacement of the pivoting door roller fittings on the thrust 
reversers.

    (b) Whenever a high engine vibration advisory occurs: Prior to 
the next flight, perform a special detailed inspection of the 
pivoting door roller fittings for cracks, using an eddy current or 
fluorescent penetrant procedure, in accordance with Airbus Service 
Bulletin A340-78-4017, dated October 14, 1999.

Corrective Action

    (c) If no crack is detected during any inspection of the 
pivoting door roller fittings on the thrust reversers as required by 
paragraph (a) or (b) of this AD, repeat the inspection at intervals 
not to exceed 500 flight hours.
    (d) If a crack is detected during any inspection of the pivoting 
door roller fittings on the thrust reversers as required by 
paragraph (a) or (b) of this AD, prior to further flight, accomplish 
either paragraph (d)(1) or (d)(2) of this AD.
    (1) Replace the fittings which are cracked with new fittings and 
repeat the inspection required by paragraph (a) at intervals not to 
exceed 500 flight hours; or
    (2) Replace all 4 fittings with new fittings and repeat the 
inspection required by paragraph (a) every 7,000 flight hours or 
1,200 flight cycles, whichever comes first.
    (e) If the inspection required by paragraph (a) or (b) cannot be 
performed, or if the inspection is performed and a fitting is found 
to be cracked, but it cannot be replaced prior to the next flight, 
perform a secondary lock functional test in accordance with Aircraft 
Maintenance Manual (AMM) 78-31-41-720-050 and deactivate the thrust 
reversers in accordance with AMM 78-30-00-040-802 and the FAA-
approved Master Minimum Equipment List.

    Note 3: Operators are reminded of the limit of three calendar 
days imposed on deactivation of thrust reversers not modified in 
accordance with BFGoodrich AOW/CFM56-97-017 and Airbus All Operators 
Telex (AOT) A340/AOT 78-06, dated May 28, 1998.

Alternative Methods of Compliance

    (f) 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, International Branch, ANM-116, 
Transport Airplane Directorate, FAA. Operators shall submit their 
requests through an appropriate FAA Principal Maintenance Inspector, 
who may add comments and then send it to the Manager, International 
Branch, ANM-116.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (g) 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.

Incorporation by Reference

    (h) Except as provided by paragraph (e) of this AD, the actions 
must be done in accordance with Airbus Service Bulletin A340-78-
4017, dated October 14, 1999. 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.

    Note 5: The subject of this AD is addressed in French 
airworthiness directive 1998-543-105(B) R2, dated November 17, 1999.

Effective Date

    (i) This amendment becomes effective on May 11, 2001.


[[Page 20910]]


    Issued in Renton, Washington, on April 16, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-9878 Filed 4-25-01; 8:45 am]
BILLING CODE 4910-13-P