[Federal Register Volume 60, Number 105 (Thursday, June 1, 1995)]
[Rules and Regulations]
[Pages 28527-28529]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-12950]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-96-AD; Amendment 39-9246; AD 95-11-13]
Airworthiness Directives; McDonnell Douglas Model MD-11 Series
Airplanes Equipped With Pratt & Whitney Model PW4460 and PW4462 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 McDonnell Douglas Model MD-11 series
airplanes. This action requires a visual inspection to detect cracks or
discrepancies in the aft mount beam assembly of the engines; and
replacement of the cracked or discrepant aft mount beam assembly with a
new assembly, or a previously inspected and re-identified assembly.
This amendment is prompted by reports of cracking in a certain aft
mount beam assembly on Airbus Model A310 series airplanes. The actions
specified in this AD are intended to prevent cracks in the aft mount
beam assembly of the engines, which could result in loss of the
capability of the aft mount beam assembly to support engine loads, and
possible separation of the engine from the airplane.
DATES: Effective June 16, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 16, 1995.
Comments for inclusion in the Rules Docket must be received on or
before July 31, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-96-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056.
The service information referenced in this AD may be obtained from
McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach,
California 90846, Attention: Technical Publications Business
Administration, Department C1-L51 (2-60). This information may be
examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue,
SW., Renton, Washington; or at the FAA, Los Angeles Aircraft
Certification Office, Transport Airplane Directorate, 3960 Paramount
Boulevard, Lakewood, California; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Wahib Mina, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712; telephone
(310) 627-5324; fax (310) 627-5210.
SUPPLEMENTARY INFORMATION: The FAA has received reports of cracking in
an aft mount beam assembly having part number (P/N) 221-0261-501
installed on Airbus Model A310 series airplanes. Metallurgical analysis
and close examination of the cracked aft mount beam assembly has
indicated this cracking is the result of physical defects, which were
caused during the forging process by one supplier. Cracks in the aft
mount beam assembly of the engines, if not detected and corrected in a
timely [[Page 28528]] manner, could result in loss of the capability of
the aft mount beam assembly to support engine loads, and possible
separation of the engine from the airplane.
Aft mount beam assemblies having P/N 221-0261-501 are also
installed on McDonnell Douglas Model MD-11 series airplanes equipped
with Pratt & Whitney PW4460 and PW4462 engines. The FAA has determined
that these airplanes are also subject to the addressed unsafe
condition.
The FAA may consider similar rulemaking action that is applicable
to Airbus Model A310 series airplanes on which the suspect mount beam
assembly also may be installed.
The FAA has reviewed and approved McDonnell Douglas Alert Service
Bulletin MD11-71A073, Revision 1, dated May 16, 1995, which describes
procedures for a one-time visual inspection to detect cracks or
discrepancies in the aft mount beam assembly, P/N 221-0261-501, of
engine numbers 1, 2, and 3. This alert service bulletin also describes
procedures for replacement of the cracked or discrepant aft mount beam
assembly with a new assembly having P/N 221-0261-503, or a previously
inspected and re-identified assembly having P/N 221-0261-501.
Since an unsafe condition has been identified that is likely to
exist or develop on certain other McDonnell Douglas Model MD-11 series
airplanes of the same type design, this AD is being issued to prevent
loss of the capability of the aft mount beam assembly to support engine
loads, and possible separation of the engine from the airplane. This AD
requires a one-time visual inspection to detect cracks or discrepancies
in the aft mount beam assembly of the engines; and replacement of the
cracked or discrepant aft mount beam assembly with a certain new
assembly, or a certain previously inspected and re-identified assembly.
The actions are required to be accomplished in accordance with the
alert service bulletin described previously.
This AD also requires that operators report results of inspection
findings, positive or negative, to the FAA.
The FAA is considering further rulemaking action to require
fluorescent penetrant and eddy current inspections of the aft mount
beam assembly, P/N 221-0261-501, of the engines within 4,000 flight
cycles after accomplishing the visual inspection required by this AD.
However, the proposed compliance time for the one-time visual
inspection is sufficiently long so that notice and time for public
comment would not be impracticable.
As a result of recent communications with the Air Transport
Association (ATA) of America, the FAA has learned that, in general,
some operators may misunderstand the legal effect of AD's on airplanes
that are identified in the applicability provision of the AD, but that
have been altered or repaired in the area addressed by the AD. The FAA
points out that all airplanes identified in the applicability provision
of an AD are legally subject to the AD. If an airplane has been altered
or repaired in the affected area in such a way as to affect compliance
with the AD, the owner or operator is required to obtain FAA approval
for an alternative method of compliance with the AD, in accordance with
the paragraph of each AD that provides for such approvals. A note has
been added to this final rule to clarify this long-standing
requirement.
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 95-NM-96-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 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. 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:
95-11-13 McDonnell Douglas: Amendment 39-9246. Docket 95-NM-96-AD.
[[Page 28529]] Applicability: Model MD-11 series airplanes,
equipped with Pratt & Whitney Model PW4460 and PW4462 engines; as
listed in McDonnell Douglas Alert Service Bulletin MD11-71A073,
Revision 1, dated May 16, 1995; 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 use the authority
provided in paragraph (d) to request approval from the FAA. This
approval may address either no action, if the current configuration
eliminates the unsafe condition; or different actions necessary to
address the unsafe condition described in this AD. Such a request
should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent loss of the capability of the aft mount beam assembly
to support engine loads, and possible separation of the engine from
the airplane, accomplish the following:
(a) Within 60 days after the effective date of this AD, perform
a visual inspection to detect cracks or discrepancies in the aft
mount beam assembly, part number (P/N) 221-0261-501, of engine
numbers 1, 2, and 3, in accordance with McDonnell Douglas Alert
Service Bulletin MD11-71A073, Revision 1, dated May 16, 1995.
(1) If no cracks or discrepancies are detected, no further
action is required by this AD.
(2) If any crack or discrepancy is detected, prior to further
flight, replace the cracked or discrepant aft mount beam assembly
with a new assembly having P/N 221-0261-503, or an assembly having
P/N 221-0261-501 that has been previously inspected and re-
identified, in accordance with paragraph 3.B., Phase 2, of the
Accomplishment Instructions of the alert service bulletin.
Replacement shall be accomplished in accordance with the procedures
specified in the alert service bulletin.
(b) Within 10 days after accomplishing the inspection required
by this AD, report inspection results, positive or negative, to the
Manager, Los Angeles Aircraft Certification Office (ACO), FAA,
Transport Airplane Directorate, 3960 Paramount Boulevard, Lakewood,
California 90712; fax (310) 627-5210. 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) As of the effective date of this AD, no person shall install
an aft mount beam assembly, P/N 221-021-501, on any airplane, unless
it has been previously inspected and re-identified in accordance
with the paragraph 3.B., Phase 2, of the Accomplishment Instructions
of McDonnell Douglas Alert Service Bulletin MD11-71A073, Revision 1,
dated May 16, 1995.
(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, Los Angeles ACO, 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, Los Angeles ACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Los Angeles ACO.
(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, replacement, and re-identification shall be
done in accordance with McDonnell Douglas Alert Service Bulletin
MD11-71A073, Revision 1, dated May 16, 1995. 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 McDonnell Douglas Corporation, 3855 Lakewood
Boulevard, Long Beach, California 90846, Attention: Technical
Publications Business Administration, Department C1-L51 (2-60).
Copies may be inspected at the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los
Angeles Aircraft Certification Office, Transport Airplane
Directorate, 3960 Paramount Boulevard, Lakewood, California; or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
(g) This amendment becomes effective on June 16, 1995.
Issued in Renton, Washington, on May 22, 1995.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-12950 Filed 5-31-95; 8:45 am]
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