[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]
BILLING CODE 4910-13-P