[Federal Register Volume 62, Number 26 (Friday, February 7, 1997)]
[Rules and Regulations]
[Pages 5753-5755]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-2852]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-NM-218-AD; Amendment 39-9921; AD 96-03-16]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model MD-11 and MD-
11F Series Airplanes
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 and MD-11F
series airplanes, that currently requires, among other things,
repetitive visual inspections to detect discrepancies of the fuel pipe
of the fuel transfer system of the tail tank and associated mounting
bracket located in the aft fuselage compartment. That AD was prompted
by reports of cracking or bending of the fuel pipe mounting support
and/or attaching bracket in the aft fuselage compartment due to a fuel
pressure surge that caused repetitive loading of this area. This
amendment adds a requirement to install a restraint on the tail tank
fuel pipe, which would terminate the repetitive visual inspections. The
actions specified by this AD are intended to prevent such cracking/
bending, which could expose the fuel pipe coupling O-ring. An exposed
O-ring could lose its sealing effect and could allow a fuel leak in the
aft fuselage compartment, which would present a fire hazard.
DATES: Effective March 14, 1997.
The incorporation by reference of McDonnell Douglas Alert Service
Bulletin MD11-28A082, dated May 14, 1996, as listed in the regulations,
was approved previously by the Director of the Federal Register as of
July 24, 1996 (61 FR 35946, July 9, 1996).
[[Page 5754]]
The incorporation by reference of McDonnell Douglas Service
Bulletin MD11-28-082, dated July 29, 1996, as listed in the
regulations, is approved by the Director of the Federal Register as of
March 14, 1997.
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, Transport Airplane Directorate, Los Angeles
Aircraft Certification Office, 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: Ray Vakili, Aerospace Engineer,
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712; telephone
(310) 627-5262; fax (310) 627-5210.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 96-14-07,
amendment 39-9691 (61 FR 35946, July 9, 1996), which is applicable to
certain McDonnell Douglas Model MD-11 and MD-11F series airplanes, was
published in the Federal Register on November 20, 1996 (61 FR 59036).
The action proposed to supersede AD 96-14-07 to continue to require
repetitive visual inspections to detect discrepancies (i.e., cracks or
deformation) of the fuel pipe of the fuel transfer system of the tail
tank and associated mounting bracket located in the aft fuselage
compartment and to verify the correct position of the fuel pipe flange,
and various follow-on actions. The action also proposed to require
installation of a restraint on the tail tank fuel pipe, which would
constitute terminating action for the repetitive visual inspection
requirements.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The commenter supports the proposed rule.
Conclusion
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
Cost Impact
There are approximately 152 McDonnell Douglas Model MD-11 and MD-
11F series airplanes of the affected design in the worldwide fleet. The
FAA estimates that 42 airplanes of U.S. registry will be affected by
this AD.
The actions that are currently required by AD 96-14-07, and
retained in this AD, take approximately 6 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 currently required actions on
U.S. operators is estimated to be $15,120, or $360 per airplane, per
inspection cycle.
The new actions that are required by this new AD will take
approximately 3 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Required parts will be supplied by the
manufacturer at no cost to the operators. Based on these figures, the
cost impact of the new requirements of this AD on U.S. operators is
estimated to be $7,560, or $180 per airplane.
The cost impact figures discussed above are 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.
Regulatory Impact
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 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 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing amendment 39-9691 (61 FR
35946, July 9, 1996), and by adding a new airworthiness directive (AD),
amendment 39-9921, to read as follows:
97-03-16 McDonnell Douglas: Amendment 39-9921. Docket 96-NM-218-AD.
Supersedes AD 96-14-07, Amendment 39-9691.
Applicability: Model MD-11 and MD-11F series airplanes,
manufacturer's fuselage numbers 0447 through 0599 inclusive;
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 request approval for an
alternative method of compliance in accordance with paragraph (f) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent the possibility of an in-flight or ground fire due to
fuel leaking from the fuel pipe coupling, accomplish the following:
Restatement of Requirements of AD 96-14-07, Amendment 39-9691
(a) Perform a visual inspection to detect discrepancies (i.e.,
cracks or deformation) of the fuel pipe of the fuel transfer system
of the tail tank and associated mounting bracket located in the aft
fuselage compartment; and to verify the correct position of the fuel
pipe flange, in accordance with McDonnell Douglas Alert Service
Bulletin MD11-28A082, dated May 14, 1996; at the time specified in
paragraph (a)(1) or (a)(2) of this AD, as applicable.
(1) For airplanes on which the modification specified in
McDonnell Douglas Service Bulletin 28-22, dated September 24,
[[Page 5755]]
1991, has been accomplished; or that have been repaired in
accordance with an FAA-approved repair procedure, as specified in
paragraph (a)(3) of AD 91-24-09, amendment 39-8095; or on which the
shroud assembly has been replaced with a serviceable part: Prior to
the accumulation of 600 flight hours, or within 60 days after July
24, 1996 (the effective date AD 96-14-07, amendment 39-9691),
whichever occurs later.
(2) For airplanes on which the modification specified in
McDonnell Douglas Service Bulletin 28-22, dated September 24, 1991,
has not been accomplished: Prior to the accumulation of 600 flight
hours, or within 60 days since accomplishment of the last visual
inspection in accordance with AD 91-24-09, amendment 39-8095;
whichever occurs first.
(b) Condition 1. No Discrepancy Found. If no discrepancy is
detected during any visual inspection required by paragraph (a) of
this AD, accomplish either paragraph (b)(1) or (b)(2) of this AD.
(1) Condition 1. Option 1. Repeat the visual inspection required
by paragraph (a) of this AD thereafter at intervals not to exceed
600 flight hours or 60 days, whichever occurs later. Or
(2) Condition 1. Option 2. Prior to further flight, install a
temporary phenolic support block assembly, shim, clamp, and bracket
between the tail tank fuel pipe and station Y=2033.750 bulkhead, in
accordance with Condition 1, Option 2, of McDonnell Douglas Alert
Service Bulletin MD11-28A082, dated May 14, 1996. Within 6 months
after accomplishment of this installation, perform a one-time
inspection to verify the correct position of the temporary support
block assembly installation in accordance with Figure 2 (Sheet 2 of
3) of the alert service bulletin.
(i) If the assembly is found to be positioned properly, repeat
the verification of the correct position of the fuel pipe flange, as
specified in paragraph (a) of this AD, thereafter at intervals not
to exceed 15 months.
(ii) If the assembly is found be improperly positioned, prior to
further flight, reposition the fuel pipe in accordance with Figure 2
(Sheet 2 of 3) of the alert service bulletin. Repeat the
verification of the correct position of the fuel pipe flange, as
specified in paragraph (a) of this AD, thereafter at intervals not
to exceed 15 months.
(c) Condition 2. Discrepancy Found; O-Ring Not Exposed. If any
discrepancy is detected, and the fuel pipe is found to be improperly
positioned, but the O-ring is not exposed, during any visual
inspection required by paragraph (a) of this AD, prior to further
flight, accomplish either paragraph (c)(1) or (c)(2) of this AD.
(1) Condition 2. Option 1. Repeat the visual inspection in
paragraph (a) of this AD thereafter at intervals not to exceed 600
flight hours or 60 days, whichever occurs later. Or
(2) Condition 2. Option 2. Prior to further flight, install a
temporary phenolic support block assembly, shim, clamp, and bracket
between the tail tank fuel pipe and station Y=2033.750 bulkhead; and
reposition the fuel pipe assembly, as applicable; in accordance with
Condition 2, Option 2, of McDonnell Douglas Alert Service Bulletin
MD11-28A082, dated May 14, 1996. Within 6 months after
accomplishment of this installation, perform a one-time inspection
to verify the correct position of the temporary support block
assembly installation in accordance with Figure 2 (Sheet 2 of 3) of
the alert service bulletin.
(i) If the assembly is found to be positioned properly, repeat
the verification of the correct position of the fuel pipe flange, as
specified in paragraph (a) of this AD, thereafter at intervals not
to exceed 15 months.
(ii) If the assembly is found to be improperly positioned, prior
to further flight, reposition the fuel pipe in accordance with
Figure 2 (Sheet 2 of 3) of the alert service bulletin. Repeat the
verification of the correct position of the fuel pipe flange, as
specified in paragraph (a) of this AD, thereafter at intervals not
to exceed 15 months.
(d) Condition 3. Discrepancy Found; O-Ring Exposed. If any
discrepancy is detected, and the fuel pipe is found to be improperly
positioned, and the O-ring is exposed, during any visual inspection
required by paragraph (a) of this AD, prior to further flight,
replace the O-ring with a new O-ring, and install a temporary
phenolic support block assembly, shim, clamp, and bracket between
the tail tank fuel pipe and station Y=2033.750 bulkhead, in
accordance with McDonnell Douglas Alert Service Bulletin MD11-
28A082, dated May 14, 1996. Within 6 months after accomplishment of
the replacement and installation, perform a one-time inspection to
verify the correct position of the temporary support block assembly
installation in accordance with Figure 2 (Sheet 2 of 3) of the alert
service bulletin.
(1) If the assembly is found to be positioned properly, repeat
the verification of the correct position of the fuel pipe flange, as
specified in paragraph (a) of this AD, thereafter at intervals not
to exceed 15 months.
(2) If the assembly is found to be improperly positioned, prior
to further flight, reposition the fuel pipe in accordance with
Figure 2 (Sheet 2 of 3) of the alert service bulletin. Repeat the
verification of the correct position of the fuel pipe flange, as
specified in paragraph (a) of this AD, thereafter at intervals not
to exceed 15 months.
New Requirements of this AD
(e) Within 24 months after the effective date of this AD,
install a restraint on the tail tank fuel pipe in accordance with
McDonnell Douglas Service Bulletin MD11-28-082, dated July 29, 1996.
Accomplishment of the installation constitutes terminating action
for the repetitive inspection requirements of this AD.
(f) 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.
(g) 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.
(h) The actions shall be done in accordance with McDonnell
Douglas Alert Service Bulletin MD11-28A082, dated May 14, 1996; and
McDonnell Douglas Service Bulletin MD11-28-082, dated July 29, 1996.
The incorporation by reference of McDonnell Douglas Alert Service
Bulletin MD11-28A082, dated May 14, 1996, 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 July 24, 1996 (61 FR 35946, July 9,
1996). The incorporation by reference of McDonnell Douglas Service
Bulletin MD11-28-082, dated July 29, 1996, is 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, Transport Airplane Directorate, Los
Angeles Aircraft Certification Office, 3960 Paramount Boulevard,
Lakewood, California; or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.
(i) This amendment becomes effective on March 14, 1997.
Issued in Renton, Washington, on January 30, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-2852 Filed 2-6-97; 8:45 am]
BILLING CODE 4910-13-p
