[Federal Register Volume 63, Number 200 (Friday, October 16, 1998)]
[Rules and Regulations]
[Pages 55522-55524]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-27480]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-288-AD; Amendment 39-10839; AD 98-21-31]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.NUREG
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to certain Airbus Model A300 series airplanes. This
action requires incorporating into the FAA-approved maintenance program
certain torque values for installing certain nuts and bolts of the
engine attachment fittings; and follow-on actions, if necessary. This
amendment is prompted by issuance of mandatory continuing airworthiness
information by a foreign civil airworthiness authority. The actions
specified in this AD are intended to prevent cracking of the nuts and
bolts of the engine attachment fittings due to overtorquing; such
cracking could propagate and result in separation of the engine from
the airplane.
DATES: Effective November 2, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 2, 1998.
Comments for inclusion in the Rules Docket must be received on or
before November 16, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-288-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
The service information referenced in this AD may be obtained from
AirbusIndustrie, 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: Norman B. Martenson, Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2110; fax(425) 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 A300 series airplanes. The DGAC advises that the October 1, 1997,
revision of the Airbus Industrie A300 Airplane Maintenance Manual
provided an incorrect, excessive torque value range of 450-500 foot
pounds, instead of the correct range of 320-340 foot pounds, for
installation of the nuts and bolts of the forward and aft attachment
fittings for CF6-50C2 engines. Such overtorquing could result in
cracking of the nuts and bolts, which, if allowed to propagate, could
cause separation of the engine from the airplane.
Explanation of Relevant Service Information
Airbus has issued All Operators Telex (AOT) A300/AOT 71-07,
datedSeptember 8, 1998. The AOT describes procedures for a one-time
inspection of the engine change job card to determine the torque value
range specified for installing the nuts and bolts of the engine forward
and aft fittings. Additionally, for airplanes for which the maintenance
program is determined to contain incorrect torque values, the AOT
describes procedures for correcting the job card, and either replacing
all nuts and bolts with new parts or inspecting the nuts and bolts for
cracks and eventually replacing all nuts and bolts with new parts. The
DGAC approved this AOT and issued French airworthiness directive T98-
376-260 (B) in order to assure the continued airworthiness of these
airplanes in France.
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 Rule
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 cracking of
the nuts and bolts of the engine attachment fittings due to
overtorquing, which could result in crack propagation and consequent
separation of the engine from the airplane. This AD requires
incorporating into the FAA-approved maintenance program certain torque
values for installing certain nuts and bolts; and accomplishing follow-
on actions specified in the AOT, if necessary.
Determination of Rule's Effective Date
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons
[[Page 55523]]
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 98-NM-288-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, 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:
98-21-31 Airbus Industrie: Amendment 39-10839. Docket 98-NM-288-AD.
Applicability: All Model A300 series airplanes equipped with
CF6-50C2 engines, 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 request approval for an
alternative method of compliance in accordance with paragraph (e) 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 cracking of the nuts and bolts of the engine
attachment fittings due to overtorquing, which could result in crack
propagation and consequent separation of the engine from the
airplane, accomplish the following:
(a) For all airplanes: Within 10 flight cycles after the
effective date of this AD, incorporate the torque value range for
the nuts and bolts of the engine forward and aft attachment fittings
into the FAA-approved maintenance program, to indicate the correct
range specified by Airbus All Operators Telex (AOT) A300/AOT 71-07,
dated September 8, 1998.
(b) For airplanes on which an engine has been replaced between
October 1, 1997, and 10 days after the effective date of this AD; if
either.
The incorrect torque value range was incorporated for
the nuts and bolts of the engine attachment fittings, as specified
in the October 1, 1997, revision of the Airbus Industrie A300
Airplane Maintenance Manual (AMM); or
Maintenance records do not indicate incorporation of
the correct torque values, as specified in Airbus All Operators
Telex (AOT) A300/AOT 71-07, dated September 8, 1998:
Within 10 flight cycles after the effective date of this AD,
accomplish either paragraph (b)(1) or (b)(2) of this AD.
(1) Replace all nuts and bolts with new parts, in accordance
with the AOT. Or
(2) Remove all nuts and bolts; perform a penetrant inspection to
detect cracking of the nuts and bolts, in accordance with the AOT;
and accomplish paragraph (b)(2)(i) or (b)(2)(ii), as applicable, of
this AD.
(i) If no crack is detected, prior to further flight, reinstall
the nuts and bolts that were removed for the inspection. Within 50
flight cycles, replace all nuts and bolts with new parts, in
accordance with the AOT.
(ii) If any crack is detected in any nut or bolt, prior to
further flight, replace the cracked nut or bolt with a new part and
reinstall the uncracked nuts and bolts. Within 50 flight cycles,
replace (with a new part) any nut and bolt that has not been
replaced within the last 50 flight cycles, in accordance with the
AOT.
(c) For airplanes on which an engine has been replaced between
October 1, 1997, and 10 days after the effective date of this AD,
using the correct torque value range for the nuts and bolts of the
engine attachment fittings, as specified in Airbus All Operators
Telex (AOT) AOT/A300 71-07, dated September 8, 1998: No further
action is required by this AD.
(d) As of the effective date of this AD, no person shall
reinstall, on any airplane, any nut or bolt that has been replaced
with a new part in accordance with paragraph (b) of this AD.
(e) 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, 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, International
Branch, ANM-116.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(f) 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.
(g) Except for the maintenance program revision provided for in
paragraph (a) of this AD, the actions shall be done in accordance
with Airbus All Operators Telex (AOT) A300/AOT 71-07, dated
September 8, 1998. This incorporation by reference was
[[Page 55524]]
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 3: The subject of this AD is addressed in French
airworthiness directive T98-376-260 (B).
(h) This amendment becomes effective on November 2, 1998.
Issued in Renton, Washington, on October 7, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-27480 Filed 10-15-98; 8:45 am]
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