[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]
BILLING CODE 4910-13-U