[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]



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


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.

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

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]
BILLING CODE 4910-13-U