[Federal Register Volume 59, Number 120 (Thursday, June 23, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-15012]
[[Page Unknown]]
[Federal Register: June 23, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 93-NM-187-AD; Amendment 39-8948; AD 94-13-08]
Airworthiness Directives; Airbus Industrie Model A310 and A300-
600 Series Airplanes Equipped With Pratt & Whitney 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 Airbus Model A310 and A300-600 series
airplanes. This action requires inspections and replacement or
reinstallation of certain aft engine mount link assemblies. This
amendment is prompted by reports of cracking in the aft engine mount
link assemblies. The actions specified in this AD are intended to
prevent loss of the capability of the aft engine mount to support
engine loads, and possible separation of the engine from the airplane.
DATES: Effective July 8, 1994.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 8, 1994.
Comments for inclusion in the Rules Docket must be received on or
before August 22, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 93-NM-187-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 A310 and A300-600 series airplanes. The DGAC advises that there
have been three reports of cracking in the aft engine mount link
assemblies, part numbers 221-0262-501 and 221-0262-503. Link assemblies
having those part numbers are installed on Model A310 and A300-600
series airplanes in conjunction with Pratt & Whitney (PW) JT9D-7R4 and
PW 4000 series engines.
Metallurgical analysis and close examination of the cracked links
has indicated a similar mode of cracking among the four cracked links
reported. This cracking is the result of physical defects, which were
caused during the forging process by one supplier. Specifically, the
cracking is a result of alloy segregation in a defective material
ingot. Two of the cracked links came from the same heat lot of 215
parts; the third cracked link came from a separate heat lot of 75
parts. Due to the random nature of alloy segregation, not all of these
290 suspect links will exhibit alloy segregation and resultant
cracking; however, cracking potentially could develop in any of them.
Cracks in the aft engine mount link assemblies, if not detected and
corrected in a timely manner, could result in loss of the capability of
the aft engine mount to support engine loads, and possible separation
of the engine from the airplane.
Airbus Industrie has issued Service Bulletin A310-71-2021, dated
March 16, 1994 (for Model A310 series airplanes), and Service Bulletin
A300-71-6019, dated March 16, 1994 (for Model A300-600 series
airplanes). These service bulletins contain general information
concerning procedures to inspect for and replace the suspect engine
mount links. These service bulletins also reference Pratt & Whitney
Service Bulletins APW7R4 71-126 (for PW JT9D-7R4 series engines) and
APW4NAC 71-138 (for PW 4000 series airplanes) for additional service
information. The Pratt & Whitney service bulletins describe procedures
for:
1. A visual inspection to determine the serial numbers of the aft
engine mount link assembly, part numbers 221-0262-501 and 221-0262-503,
at all three link positions (left outboard, right outboard, and
inboard); and to determine the serial numbers of the links.
2. Removal of any suspect link found during the visual inspection;
a fluorescent penetrant inspection and an eddy current inspection to
detect cracks in the suspect link; and replacement of any cracked or
defective suspect link with a link having a serial number that is not
within the suspect serial number groups.
3. Replacement of any suspect link that is not cracked or defective
with a link having a serial number that is not within the suspect
serial number groups, or reidentification and reinstallation of the
uncracked suspect link.
The DGAC classified the Airbus service bulletins as mandatory and
issued French Airworthiness Directive 94-074-159(B), dated March 30,
1994, in order to assure the continued airworthiness of these airplanes
in France.
These airplane models are manufactured in France and are 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.
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 loss of the
capability of the aft engine mount to support engine loads, and
possible separation of the engine from the airplane.
This AD requires a visual inspection of the aft engine mount link
assembly, part numbers 221-0262-501 and 221-0262-503, at all three link
positions (left outboard, right outboard, and inboard) to determine the
serial numbers of the links. If any suspect link is found, operators
are required to remove the link and perform both a fluorescent
penetrant inspection and an eddy current inspection of it to detect
cracks and other defects, and to replace any cracked or defective
suspect link with a link having a serial number that is not within the
suspect serial number groups. If no crack or defect is found in the
link, it may either be replaced with a non-suspect link, or
reidentified and reinstalled. The actions are required to be
accomplished in accordance with the Airbus service bulletin described
previously.
This AD also requires that operators report certain inspection
findings to the FAA.
The FAA has initiated a similar rulemaking action that is
applicable to McDonnell Douglas Model MD-11 series airplanes on which
the suspect links may also be installed.
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 notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 93-NM-187-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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and 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. 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:
94-13-08 Airbus Industrie: Amendment 39-8948. Docket 93-NM-187-AD.
Applicability: Model A310 and A300-600 series airplanes;
equipped with Pratt & Whitney (PW) JT9D-7R4 series engines or PW
4000 series engines; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent the loss of the capability of aft engine mount to
support engine loads, and possible separation of the engine from the
airplane, accomplish the following:
(a) Within 120 days after the effective date of this AD, perform
a visual inspection of the aft engine mount link assembly, part
numbers 221-0262-501 and 221-0262-503, at all three link positions
(left outboard, right outboard, and inboard) to determine the serial
numbers of the links and to identify any suspect link that is
installed, in accordance with Airbus Service Bulletin A310-71-2021,
dated March 16, 1994 (for Model A310 series airplanes), or Airbus
Service Bulletin A300-71-6019, dated March 16, 1994 (for Model A300-
600 series airplanes), as applicable. Suspect links are those links
having serial numbers WPC0001 through WPC1063 inclusive, or M1064
through M1255 inclusive. If no suspect link is installed, no further
action is required by this AD.
Note 1: Links having serial numbers M1255 and below with the
``M'' prefix are from the same forging supplier as links having the
``WPC'' prefix.
(b) If any suspect link is found during the inspection required
by paragraph (a) of this AD, prior to further flight, remove the
suspect link, and perform a fluorescent penetrant inspection and an
eddy current inspection to detect cracks or other defects in the
suspect link, in accordance with Airbus Service Bulletin A310-71-
2021, dated March 16, 1994 (for Model A310 series airplanes), or
Airbus Service Bulletin A300-71-6019, dated March 16, 1994 (for
Model A300-600 series airplanes), as applicable.
(1) If any crack or defect is found in the link, prior to
further flight, replace it with a link having a serial number that
is not within the suspect serial number groups, in accordance with
the service bulletin.
(2) If no crack or defect is found in the link, prior to further
flight, replace it with a link having a serial number that is not
within the suspect serial number groups, or reidentify and reinstall
the uncracked suspect link in accordance with the service bulletin.
No further action is required by this AD for that link.
(c) Within 10 days after accomplishing the inspection required
by paragraph (a) of this AD, submit a report of inspection findings,
including the information specified in paragraphs (c)(1), (c)(2),
and (c)(3) of this AD, to the Manager, Standardization Branch, ANM-
113, FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, Washington 98055-4056; fax (206) 227-1320. 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.
(1) The serial number of any suspect link found.
(2) The aircraft fuselage serial number on which the suspect
link was found.
(3) The results of inspections required by paragraph (b) of this
AD.
(d) 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.
(e) 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.
(f) The inspection and replacement shall be done in accordance
with Airbus Service Bulletin A310-71-2021, dated March 16, 1994 (for
Model A310 series airplanes); or Airbus Service Bulletin A300-71-
6019, dated March 16, 1994 (for Model A300-600 series airplanes); as
applicable. 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.
(g) This amendment becomes effective on July 8, 1994.
Issued in Renton, Washington, on June 15, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-15012 Filed 6-22-94; 8:45 am]
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