[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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