AD 2000-23-17

[Federal Register Volume 65, Number 226 (Wednesday, November 22, 2000)]
[Rules and Regulations]
[Pages 70297-70300]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-29377]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-243-AD; Amendment 39-11990; AD 2000-23-17]
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 opening the circuit breaker 
of the pneumatic sense line heater tape, installing an inoperative 
ring, and coiling and stowing the electrical wire to the circuit 
breaker of the pneumatic sense line heater tape. That AD also provides 
for an optional inspection, which, if accomplished, constitutes 
terminating action for deactivation of the pneumatic sense line heater 
tape. This amendment requires repetitive inspections of the subject 
area and corrective actions, if necessary, and provides for an optional 
terminating modification(s) for the repetitive inspection requirements. 
This amendment is prompted by the FAA's determination that the one-time 
optional terminating inspection in the existing AD does not adequately 
detect chafing, electrical arcing, or inadequate clearance of the 
subject area. The actions specified by this AD are intended to detect 
and correct such inadequate clearance, which could result in a hole in 
the fuel feed pipe caused by electrical arcing, and consequent fuel 
leakage and possible ignition of the fuel vapors.

DATES: Effective December 27, 2000.
    The incorporation by reference of certain publications, as listed 
in the regulations, is approved by the Director of the Federal Register 
as of December 27, 2000.
    The incorporation by reference of McDonnell Douglas Alert Service 
Bulletin MD11-36A030, dated April 2, 1998, as listed in the 
regulations, was approved previously by the Director of the Federal 
Register as of April 28, 1998 (63 FR 20066, April 23, 1998).

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Aircraft Group, Long Beach Division, 
3855 Lakewood Boulevard, Long Beach, California 90846, Attention: 
Technical Publications Business Administration, Dept. 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 the FAA, 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: Stephen Kolb, Senior Aerospace 
Engineer, Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712; telephone (562) 627-5244; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 98-08-11, 
amendment 39-10491 (63 FR 20066, April 23, 1998), which is applicable 
to certain McDonnell Douglas Model MD-11 and MD-11F series airplanes, 
was published in the Federal Register on July 13, 2000 (65 FR 43265). 
The action proposed to continue to require opening the circuit breaker 
of the pneumatic sense line heater tape, installing an inoperative 
ring, and coiling and stowing the electrical wire to the circuit 
breaker of the pneumatic sense line heater tape. The action also 
proposed to require repetitive inspections of the subject area and 
corrective actions, if necessary, and would provide for an optional 
terminating modification(s) for the repetitive inspection requirements.

Comments

    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 states no objection to the proposed rule.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air

[[Page 70298]]

safety and the public interest require the adoption of the rule as 
proposed.

Cost Impact

    There are approximately 174 Model MD-11 and MD-11F series airplanes 
of the affected design in the worldwide fleet. The FAA estimates that 
67 airplanes of U.S. registry will be affected by this AD.
    The modification that is currently required by AD 98-08-11, and 
retained in this AD, takes approximately 1 work hour 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 $4,020, or $60 per airplane.
    The new inspection required by this AD action will take 
approximately 1 work hour per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the new inspection required by this AD on U.S. operators is 
estimated to be $4,020, or $60 per airplane, per inspection cycle.
    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. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.
    Should an operator elect to accomplish the optional terminating 
action provided by paragraph (d)(1) of this AD, it would take 
approximately 4 work hours to accomplish, at an average labor rate of 
$60 per work hour. The cost of required parts would be approximately 
$4,500 per airplane. Based on these figures, the cost impact of this 
optional terminating action would be $4,740 per airplane.
    Should an operator elect to accomplish the optional terminating 
action provided by paragraph (d)(2) of this AD, it would take 
approximately 1 work hour to accomplish, at an average labor rate of 
$60 per work hour. The cost of required parts would be approximately 
$50 per airplane. Based on these figures, the cost impact of this 
optional terminating action would be $110 per airplane.
    Should an operator elect to accomplish the optional terminating 
action provided by paragraph (d)(3) of this AD, it would take 
approximately 2 work hours to accomplish, at an average labor rate of 
$60 per work hour. The cost of required parts would be approximately 
$2,500 per airplane. Based on these figures, the cost impact of this 
optional terminating action would be $2,620 per airplane.
    Should an operator elect to accomplish the optional terminating 
action provided by paragraph (d)(4) of this AD, it would take 
approximately 4 work hours to accomplish, at an average labor rate of 
$60 per work hour. The cost of required parts would be approximately 
$50 per airplane. Based on these figures, the cost impact of this 
optional terminating action would be $290 per airplane.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 39-10491 (63 FR 
20066, April 23, 1998), and by adding a new airworthiness directive 
(AD), amendment 39-11990, to read as follows:
2000-23-17  McDonnell Douglas: Amendment 39-11990. Docket 99-NM-243-
AD. Supersedes AD 98-08-11, Amendment 39-10491.

    Applicability: Model MD-11 and MD-11F series airplanes, having 
manufacturer's fuselage numbers 0447 through 0552 inclusive, and 
0554 through 0620 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 
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 detect and correct inadequate clearance between the fuel feed 
pipe of the number 2 engine and the pneumatic sense line heater 
tape, which could result in a hole in the fuel feed pipe caused by 
electrical arcing, and consequent fuel leakage and possible ignition 
of the fuel vapors, accomplish the following:

Restatement of Requirements of AD 98-08-11

Modification

    (a) Within 7 days after April 28, 1998 (the effective date of AD 
98-08-11, amendment 39-10491), open the circuit breaker of the 
pneumatic sense line heater tape, install an inoperative ring, and 
coil and stow the electrical wire to the circuit breaker of the 
pneumatic sense line heater tape, in accordance with Phase 1 of the 
Accomplishment Instructions of McDonnell Douglas Alert Service 
Bulletin MD11-36A030, dated April 2, 1998; Revision 01, dated 
September 28, 1998; Revision 02, dated July 27, 1999; or Revision 
03, dated December 14, 1999. Accomplishment of these actions 
deactivates the pneumatic sense line heater tape.

    Note 2: The pneumatic sense line heater tape of the number 2 
engine has been deactivated. This deactivation may cause a nuisance 
shutdown of the bleed air system of the number 2 engine at top of 
descent.

New Requirements of This AD

Repetitive Inspections

    (b) Except as provided in paragraph (d) of this AD, within 6 
months after the effective date of this AD, perform a detailed 
visual

[[Page 70299]]

inspection to detect chafing, electrical arcing, or inadequate 
clearance of the pneumatic sense lines and fuel feed pipe of the 
number 2 engine, in accordance with Phase 2 of the Accomplishment 
Instructions of McDonnell Douglas Alert Service Bulletin MD11-
36A030, Revision 03, dated December 14, 1999. Repeat the inspection 
thereafter at intervals not to exceed 5,000 flight hours or 18 
months, whichever occurs later. Accomplishment of the detailed 
visual inspection constitutes terminating action for the 
deactivation requirements of paragraph (a) of this AD.

    Note 3: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc. may be used. Surface cleaning and 
elaborate access procedures may be required.''


    Note 4: Detailed visual inspections accomplished before the 
effective date of this AD in accordance with McDonnell Douglas Alert 
Service Bulletin MD11-36A030, dated April 2, 1998, Revision 01, 
dated September 28, 1998, or Revision 02, dated July 27, 1999; are 
considered acceptable for compliance with the requirements of 
paragraph (b) of this AD.

Corrective Actions

    (c) If any discrepancy (i.e., as identified in Conditions 1, 2, 
3, 4, and 5 of the Accomplishment Instructions of McDonnell Douglas 
Alert Service Bulletin MD11-36A030, Revision 03, dated December 14, 
1999) is detected during any inspection required by paragraph (b) of 
this AD, before further flight, perform the applicable corrective 
actions in accordance with Conditions 1, 2, 3, 4, or 5 of the 
Accomplishment Instructions of McDonnell Douglas Alert Service 
Bulletin MD11-36A030, Revision 03, dated December 14, 1999, except 
as indicated in paragraphs (c)(1) and (c)(2) of this AD.
    (1) Accomplishment of the modification of the high stage pilot 
valve of the left and right wings in accordance with McDonnell 
Douglas Service Bulletin MD11-36-018 R01, Revision 1, dated July 18, 
1995, is NOT necessary to comply with the applicable corrective 
action in Condition 5 of the Accomplishment Instructions of the 
service bulletin.
    (2) Accomplishment of the modification and reidentification of 
the pilot pressure regulator valve of the left and right wings in 
accordance with McDonnell Douglas Service Bulletin MD11-36-025 R01, 
Revision 01, dated July 31, 1997, is NOT necessary to comply with 
the applicable corrective action in Condition 5 of the 
Accomplishment Instructions of the service bulletin.

Optional Actions

    (d) Accomplishment of the action(s) specified in paragraphs 
(d)(1), (d)(2), (d)(3), and (d)(4) of this AD, as applicable, 
constitutes terminating action for the repetitive inspection 
requirements of paragraph (b) of this AD.
    (1) For airplanes having manufacturer's fuselage numbers 0447 
through 0552 inclusive, and 0554 through 0573 inclusive: Before or 
in conjunction with the actions specified in paragraph (d)(2) of 
this AD, modify the high stage pilot valve located in the aft 
accessory compartment (including purging the sense lines and 
revising wiring of the high stage pilot valve), in accordance with 
McDonnell Douglas Service Bulletin MD11-36-018 R01, Revision 1, 
dated July 18, 1995.

    Note 5: In addition to the procedures for modification of the 
high stage pilot valve located in the aft accessory compartment, 
McDonnell Douglas Service Bulletin MD11-36-018 R01, Revision 1, 
dated July 18, 1995, also describes procedures for modification of 
the high stage pilot valve of the left and right wings. 
Accomplishment of modification of the high stage pilot valve of the 
left and right wings is NOT necessary to comply with the optional 
action provided by paragraph (d)(1) of this AD.


    Note 6: Modification of the high stage pilot valve of the aft 
accessory compartment accomplished before the effective date of this 
AD in accordance with McDonnell Douglas Service Bulletin MD11-36-
018, dated March 28, 1995, is considered acceptable for compliance 
with the actions specified in paragraph (d)(1) of this AD.

    (2) For airplanes having manufacturer's fuselage numbers 0447 
through 0552 inclusive, and 0554 through 0608 inclusive: Disconnect 
and splice together the heater tape wires of the pneumatic sense 
lines for the high stage and fan air valves from the terminals 
strips in the lower vertical stabilizer, in accordance with 
McDonnell Douglas Service Bulletin MD11-36-026, dated September 30, 
1996.
    (3) For airplanes having manufacturer's fuselage numbers 0447 
through 0552 inclusive, and 0554 through 0608 inclusive: Before or 
in conjunction with the actions specified in paragraph (d)(4) of 
this AD, modify and reidentify the pilot pressure regulator valve 
located in the aft accessory compartment (including purging the 
sense lines and revising the wiring of the pilot pressure regulator 
valve), in accordance with McDonnell Douglas Service Bulletin MD11-
36-025 R01, Revision 01, dated July 31, 1997.

    Note 7: In addition to the procedures for modification and 
reidentification of the pilot pressure regulator valve located in 
the aft accessory compartment, McDonnell Douglas Service Bulletin 
MD11-36-025 R01, Revision 01, dated July 31, 1997, also describes 
procedures for modification and reidentification of the pilot 
pressure regulator valve of the left and right wings. Accomplishment 
of the modification and reidentification of the pilot pressure 
regulator valve of the left and right wings is NOT necessary to 
comply with the optional action provided by paragraph (d)(3) of this 
AD.


    Note 8: Modification and reidentification of the pilot pressure 
regulator valve of the aft accessory compartment accomplished before 
the effective date of this AD in accordance with McDonnell Douglas 
Service Bulletin MD11-36-025, dated February 14, 1997; is considered 
acceptable for compliance with the actions specified in paragraph 
(d)(3) of this AD.

    (4) For airplanes having manufacturer's fuselage numbers 0447 
through 0464 inclusive, 0466 through 0552 inclusive, and 0554 
through 0620 inclusive: Disconnect the heater tape wires from their 
respective terminal strips and splice the wire ends together, in 
accordance with McDonnell Douglas Service Bulletin MD11-36-028, 
dated December 7, 1998.

Reporting

    (e) Within 10 days after accomplishing any inspection required 
by paragraph (b) of this AD, submit a report of the inspection 
results (only negative findings) to the Manager, Los Angeles 
Aircraft Certification Office (ACO), FAA, 3960 Paramount Boulevard, 
Lakewood, California 90712-4137; fax (562) 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.

Alternative Methods of Compliance

    (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 ACO. 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 9: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

Special Flight Permits

    (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.

Incorporation by Reference

    (h) The actions shall be done in accordance with McDonnell 
Douglas Alert Service Bulletin MD11-36A030, dated April 2, 1998; 
McDonnell Douglas Alert Service Bulletin MD11-36A030, Revision 01, 
dated September 28, 1998; McDonnell Douglas Alert Service Bulletin 
MD11-36A030, Revision 02, dated July 27, 1999; McDonnell Douglas 
Alert Service Bulletin MD11-36A030, Revision 03, dated December 14, 
1999; McDonnell Douglas Service Bulletin MD11-36-018 R01, Revision 
1, dated July 18, 1995; McDonnell Douglas Service Bulletin MD11-36-
026, dated September 30, 1996; McDonnell Douglas Service Bulletin 
MD11-36-025 R01, Revision 01, dated July 31, 1997; and McDonnell 
Douglas Service Bulletin MD11-36-028, dated December 7, 1998; as 
applicable.
    (1) The incorporation by reference of McDonnell Douglas Alert 
Service Bulletin MD11-36A030, Revision 01, dated

[[Page 70300]]

September 28, 1998; McDonnell Douglas Alert Service Bulletin MD11-
36A030, Revision 02, dated July 27, 1999; McDonnell Douglas Alert 
Service Bulletin MD11-36A030, Revision 03, dated December 14, 1999; 
McDonnell Douglas Service Bulletin MD11-36-018 R01, Revision 1, 
dated July 18, 1995; McDonnell Douglas Service Bulletin MD11-36-026, 
dated September 30, 1996; McDonnell Douglas Service Bulletin MD11-
36-025 R01, Revision 01, dated July 31, 1997; and McDonnell Douglas 
Service Bulletin MD11-36-028, dated December 7, 1998; is approved by 
the Director of the Federal Register in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51.
    (2) The incorporation by reference of McDonnell Douglas Alert 
Service Bulletin MD11-36A030, dated April 2, 1998, was approved 
previously by the Director of the Federal Register as of April 28, 
1998 (63 FR 20066, April 23, 1998).
    (3) Copies may be obtained from Boeing Commercial Aircraft 
Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, 
California 90846, Attention: Technical Publications Business 
Administration, Dept. C1-L51 (2-60). Copies may be inspected at FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the the FAA, 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.

Effective Date

    (i) This amendment becomes effective on December 27, 2000.

    Issued in Renton, Washington, on November 9, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-29377 Filed 11-21-00; 8:45 am]
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