Airworthiness Directives; Airbus Model A310 Series Airplanes Equipped With General Electric Model CF6-80A3 Series Engines

[Federal Register Volume 63, Number 111 (Wednesday, June 10, 1998)]
[Rules and Regulations]
[Pages 31614-31616]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-15250]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-182-AD; Amendment 39-10578; AD 98-12-24]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 Series Airplanes 
Equipped With General Electric Model CF6-80A3 Series Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Airbus Model A310 series airplanes. This 
action requires a one-time inspection to detect

[[Page 31615]]

cracked or broken links of the aft engine mounts, and replacement of 
any cracked or broken link with a serviceable link. 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 detect and correct cracking of the links of the 
aft engine mounts, which could result in failure of the aft engine 
attachment and consequent separation of the engine from the airplane.

DATES: Effective June 25, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 25, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before July 10, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-182-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: 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, notified the 
FAA that an unsafe condition may exist on certain Airbus Model A310 
series airplanes. The DGAC advises that, during a routine maintenance 
inspection of a General Electric Model CF6-80A3 series engine for an 
Airbus Model A310 series airplane, a crack was discovered on the left-
hand link of the aft engine mount assembly. The crack measured 10 mm in 
length and was located at the upper end of the link, at the gearing 
location. The cause of the crack is still under investigation. This 
condition, if not corrected, could result in failure of the aft engine 
attachment and consequent separation of the engine from the airplane.

Explanation of Relevant Service Information

    Airbus has issued All Operators Telex (AOT) 71 06, dated October 
21, 1997, which describes procedures for a one-time detailed visual 
inspection to detect cracked or broken links of the aft engine mounts, 
and replacement of any cracked or broken link with a serviceable link. 
The DGAC classified this AOT as mandatory and issued French telegraphic 
airworthiness directive T97-324-234(B), dated October 22, 1997, and 
airworthiness directive 97-324-234(B), dated November 5, 1997; 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 detect and correct 
cracking of the links of the aft engine mounts, which could result in 
failure of the aft engine attachment and consequent separation of the 
engine from the aiplane. This AD requires accomplishment of the actions 
specified in the AOT described previously. This AD also requires that 
operators report results of inspection findings (positive and negative) 
to Airbus.

Interim Action

    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking.

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 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-182-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

[[Page 31616]]

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:

98-12-24  Airbus Industrie: Amendment 39-10578. Docket 98-NM-182-AD.

    Applicability: Model A310 series airplanes, equipped with 
General Electric Model CF6-80A3 series 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 (c) 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 links of the aft engine 
mounts, which could result in failure of the aft engine attachment 
and consequent separation of the engine from the airplane, 
accomplish the following:
    (a) Within 5 days after the effective date of this AD, perform a 
one-time detailed visual inspection to detect cracked or broken 
links of the aft engine mounts, in accordance with Airbus All 
Operators Telex (AOT) 71 06, dated October 21, 1997. If any cracked 
or broken link is detected, prior to further flight, replace the 
cracked or broken link with a serviceable link, in accordance with 
the AOT.
    (b) Within 10 days after the effective date of this AD, submit a 
report of the inspection results (positive and negative) to Airbus 
Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France. Information collection requirements contained in this 
regulation have been approved by the Office of Management and Budget 
(OMB) under the provisions of the Paperwork Reduction Act of 1980 
(44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 
2120-0056.
    (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, 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.

    (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 actions shall be done in accordance with Airbus All 
Operators Telex 71 06, dated October 21, 1997. 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 3: The subject of this AD is addressed in French 
telegraphic airworthiness directive T97-324-234(B), dated October 
22, 1997, and airworthiness directive 97-324-234(B), dated November 
5, 1997.

    (f) This amendment becomes effective on June 25, 1998.

    Issued in Renton, Washington, on June 3, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-15250 Filed 6-9-98; 8:45 am]
BILLING CODE 4910-13-U

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T05:01:51.054637+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

fbf8a346284bee064e19b9986ef772336371f7772e14c687cc08e9cd649ae1da

Text SHA-256

aa1050b06958648617ad5be888a87c33ca564817bcbf971453ba23d9cf58b2b3