[Federal Register Volume 60, Number 122 (Monday, June 26, 1995)]
[Proposed Rules]
[Pages 32926-32929]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-15517]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-97-AD]


Airworthiness Directives; McDonnell Douglas Model MD-11 Series 
Airplanes Equipped With Pratt & Whitney Model PW4460 and PW4462 Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain McDonnell Douglas 
Model MD-11 series airplanes, that currently 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. That amendment was prompted by reports of 
cracking in a certain aft mount beam assembly on Airbus Model A310 
series airplanes. This action would continue to require the visual 
inspection, and corrective actions for findings of cracking or 
discrepancies. This action would require additional inspections to 
detect cracks or discrepancies in the subject area, and follow-on 
actions. The actions specified by the proposed 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 [[Page 32927]] loads, and possible separation of the 
engine from the airplane.

DATES: Comments must be received by August 21, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-97-AD, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056. Comments may be inspected at this location 
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal 
holidays.
    The service information referenced in the proposed rule 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, Transport Airplane 
Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount 
Boulevard, Lakewood, California.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed 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 above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this notice may be changed in 
light of the comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal 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 95-NM-97-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-103, Attention: Rules 
Docket No. 95-NM-97-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On May 22, 1995, the FAA issued AD 95-11-13, amendment 39-9246 (60 
FR 28527, June 1, 1995), applicable to certain McDonnell Douglas Model 
MD-11 series airplanes, to require 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. That action was prompted by reports of 
cracking in an aft mount beam assembly having part number (P/N) 221-
0261-501 on Airbus Model A310 series airplanes. The requirements of 
that 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.
    Aft mount beam assemblies having P/N 221-0261-501 also are 
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.
    In the preamble to AD 95-11-13, the FAA indicated that it intended 
to supersede that AD 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 that AD. This action proposes to require the 
addition of these inspection requirements.
    The FAA previously 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.
    As a follow-on action to the visual inspection, this service 
bulletin describes procedures for etch fluorescent penetrant and eddy 
current inspections to detect cracks or discrepancies in the aft mount 
beam assembly, P/N 221-0261-501, of engine numbers 1, 2, and 3. This 
service bulletin also describes procedures for re-identifying and 
installing the aft mount beam assembly, if no cracks or discrepancies 
are detected during the fluorescent penetrant and eddy current 
inspections; and for replacement of any cracked or discrepant assembly 
found during these inspections.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would supersede AD 95-11-13 to continue to require 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, 
and corrective actions for findings of cracking or discrepancies. The 
proposed AD would also require etch fluorescent penetrant and eddy 
current inspections to detect cracks or discrepancies in the subject 
area, and follow-on actions. The actions would be required to be 
accomplished in accordance with the alert service bulletin described 
previously.
    This proposed AD would also require that operators report results 
of any inspection findings, positive or negative, to the FAA.
    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 included in this notice to clarify this long-standing requirement. 
[[Page 32928]] 
    There are approximately 57 Model MD-11 series airplanes equipped 
with Pratt & Whitney Model PW4460 and PW4462 engines of the affected 
design in the worldwide fleet. The FAA estimates that 17 airplanes of 
U.S. registry would be affected by this proposed AD.
    The visual inspection that was previously required by AD 95-11-13, 
and retained in this proposal, would take approximately 2 work hours 
per airplane to accomplish, at an average labor rate of $60 per work 
hour. Based on these figures, the total cost impact of the visual 
inspection requirement on U.S. operators is estimated to be $2,040, or 
$120 per airplane. The FAA estimates that all affected U.S. operators 
have already accomplished this action; therefore, the future cost 
impact of this requirement is minimal.
    The fluorescent penetrant and eddy current inspections that would 
be required by this proposal would take approximately 15 work hours per 
airplane to accomplish, at an average labor rate of 60 per work hour. 
Based on these figures, the total cost impact of the proposed 
fluorescent penetrant and eddy current inspection requirements of this 
AD on U.S. operators is estimated to be $15,300, or $900 per airplane.
    The total cost impact figure discussed above is based on 
assumptions that no operator has yet accomplished any of the proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.
    The regulations proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, will not have a significant economic impact, 
positive or negative, on a substantial number of small entities under 
the criteria of the Regulatory Flexibility Act. A copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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 removing amendment 39-9246 (60 FR 
28527, June 1, 1995), and by adding a new airworthiness directive (AD), 
to read as follows:

McDonnell Douglas: Docket 95-NM-97-AD. Supersedes AD 95-11-13, 
Amendment 39-9246.

    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 (e) of this AD 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 June 16, 1995 (the effective date of AD 
95-11-13, amendment 39-9246), 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 paragraph (a) of 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 4,000 flight cycles after accomplishing the visual 
inspection required by paragraph (a) of this AD, perform etch 
fluorescent penetrant and eddy current inspections to detect cracks 
or discrepancies in the aft mount beam assembly, 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, prior to further 
flight, re-identify and install the aft mount beam assembly in 
accordance with the alert service bulletin.
    (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.
    (c) Within 10 days after accomplishing any 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.
    (d) As of June 16, 1995 (the effective date of AD 95-11-13, 
amendment 39-9246), no person shall install an aft mount beam 
assembly, P/N 221-0261-501, on any airplane, unless it has been 
previously inspected and re-identified in accordance with paragraph 
3.B., Phase 2, of the Accomplishment Instructions of McDonnell 
Douglas Alert Service Bulletin MD11-71A073, Revision 1, dated May 
16, 1995.
    (e) 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 
[[Page 32929]] 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.

    (f) 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.

    Issued in Renton, Washington, on June 20, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-15517 Filed 6-23-95; 8:45 am]
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