[Federal Register Volume 61, Number 13 (Friday, January 19, 1996)]
[Rules and Regulations]
[Pages 1278-1279]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-533]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-97-AD; Amendment 39-9478; AD 96-01-02]


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.

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SUMMARY: This amendment supersedes 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. This new amendment requires additional inspections 
to detect cracks or discrepancies in the subject area, and various 
follow-on actions. The actions specified by this amendment 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 February 20, 1996.
    The incorporation by reference of McDonnell Douglas Alert Service 
Bulletin MD11-71A073, Revision 2, dated October 10, 1995, as listed in 
the regulations is approved by the Director of the Federal Register as 
of February 20, 1996.
    The incorporation by reference of McDonnell Douglas Alert Service 
Bulletin MD11-71A073, Revision 1, dated May 16, 1995, as listed in the 
regulations, was approved previously by the Director of the Federal 
Register as of June 16, 1995 (60 FR 28527, June 1, 1995).

ADDRESSES: 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 Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 95-11-13, 
amendment 39-9246 (60 FR 28527, June 1, 1995), which is applicable to 
certain McDonnell Douglas Model MD-11 series airplanes, was published 
in the Federal Register on June 26, 1995 (60 FR 32926). [A correction 
of that rule was published in the Federal Register on June 15, 1995 (60 
FR 31387).] The action proposed to continue to require the one-time 
visual inspection to detect cracks or discrepancies in the aft mount 
beam assembly of the engines; and replacement of the aft mount beam 
assembly, if necessary. It also proposed to add etch fluorescent 
penetrant inspections as well as eddy current inspections to detect 
cracks or discrepancies in the aft mount beam assembly of the engines; 
and to require various follow-on actions.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    One commenter supports the proposed rule.
    Two commenters request that the proposed rule be revised to cite 
the latest revision of McDonnell Douglas Alert Service Bulletin MD11-
71A073 as an additional source of service information. The FAA concurs. 
Since the issuance of the proposed rule, the FAA has reviewed and 
approved Revision 2 of McDonnell Douglas Alert Service Bulletin MD11-
71A073, dated October 10, 1995. Except for minor edits, this revised 
service bulletin is essentially identical to Revision 1 and does not 
entail any additional work on the part of affected operators. The FAA 
has revised the final rule to reference Revision 2 of the service 
bulletin as an additional source of service information.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.
    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 will be affected by this AD.
    The visual inspection that was previously required by AD 95-11-13, 
and retained in this AD, takes approximately 2 work hours per airplane 
to accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the 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, any future cost impact of this requirement is 
expected to be minimal.
    The fluorescent penetrant and eddy current inspections that are 
required by this new AD will take approximately 15 work hours per 
airplane to accomplish, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the fluorescent penetrant 
and eddy current inspection requirements on U.S. operators is estimated 
to be $15,300, or $900 per airplane, per inspection cycle. This cost 
impact figure is based on assumptions that no operator has yet 
accomplished any of the requirements of this AD action, and that no 
operator would accomplish those actions in the future if this AD were 
not adopted.
    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.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under 

[[Page 1279]]
Executive Order 12866; (2) is not a ``significant rule'' under DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) 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 final evaluation has been prepared 
for this action and it is contained in the Rules Docket. A copy of it 
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 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-9246 (60 FR 
31387, June 15, 1995), and by adding a new airworthiness directive 
(AD), amendment 39-9478, to read as follows:

96-01-02  McDonnell Douglas: Amendment 39-9478. 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 
otherwise 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, or Revision 2, dated October 10, 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 either alert service bulletin.
    (b) Within 4,000 flight cycles after accomplishing any 
inspection required by 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, or Revision 2, 
dated October 10, 1995.
    (1) If no crack or discrepancy is 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, or Revision 2, dated October 10, 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 Aircraft Certification 
Office (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.

    (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.
    (g) The inspections and replacement shall be done in accordance 
with McDonnell Douglas Alert Service Bulletin MD11-71A073, Revision 
1, dated May 16, 1995, or McDonnell Douglas Alert Service Bulletin 
MD11-71A073, Revision 2, dated October 10, 1995. The incorporation 
by reference of McDonnell Douglas Alert Service Bulletin MD11-
71A073, Revision 2, dated October 10, 1995, is approved by the 
Director of the Federal Register in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51. The incorporation by reference of McDonnell 
Douglas Alert Service Bulletin MD11-71A073, Revision 1, dated May 
16, 1995, was approved previously by the Director of the Federal 
Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of 
as of June 16, 1995 (60 FR 28527, June 1, 1995). 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.
    (h) This amendment becomes effective on February 20, 1996.

    Issued in Renton, Washington, on December 27, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-533 Filed 1-18-96; 8:45 am]
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