[Federal Register Volume 68, Number 246 (Tuesday, December 23, 2003)]
[Rules and Regulations]
[Pages 74171-74172]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-31439]



[[Page 74171]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-169-AD; Amendment 39-13400; AD 2003-11-15 R1]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-90-30 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment revises an existing airworthiness directive 
(AD), applicable to all McDonnell Douglas Model MD-90-30 airplanes, 
that currently requires replacing the lanyards on the pressure relief 
door for the thrust reverser with new, improved lanyards, and doing 
associated modifications. The actions specified by that AD are intended 
to ensure that the lanyards on the pressure relief door have adequate 
strength. Lanyards of inadequate strength could allow the pressure 
relief door to detach from the thrust reverser in the event that an 
engine bleed air duct bursts, which could result in the detached door 
striking and damaging the horizontal stabilizer, and consequent reduced 
controllability of the airplane. This amendment is prompted by the fact 
that a certain paragraph of the existing AD prohibits installation of 
certain part numbers of lanyards; the numbers listed in that paragraph 
correspond to new, improved lanyards that are acceptable for 
installation. This amendment will correct these part numbers to 
prohibit installation of suspect lanyards while allowing installation 
of the new, improved lanyards. This action is intended to address the 
identified unsafe condition.

DATES: Effective January 27, 2004.
    The incorporation by reference of Boeing Service Bulletin MD90-78-
048, dated February 15, 2001, as listed in the regulations, was 
approved previously by the Director of the Federal Register as of July 
9, 2003 (68 FR 33355, June 4, 2003).

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: Data 
and Service Management, Dept. C1-L5A (D800-0024); and Rohr, Inc., 850 
Lagoon Drive, Chula Vista, California 91910-2098. 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, 
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, Aerospace Engineer, 
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
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 revising AD 2003-11-15, 
amendment 39-13174 (68 FR 33355, June 4, 2003), which is applicable to 
all McDonnell Douglas Model MD-90-30 airplanes, was published in the 
Federal Register on August 21, 2003 (68 FR 50491). The action proposed 
to continue to require replacing the lanyards on the pressure relief 
door for the thrust reverser with new, improved lanyards, and doing 
associated modifications. The action also proposed to prohibit 
installation of certain pressure relief door lanyards.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Changes to 14 CFR part 39/Effect on the AD

    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness 
directives system. The regulation now includes material that relates to 
altered products, special flight permits, and alternative methods of 
compliance (AMOCs). However, for clarity and consistency in this final 
rule, we have retained the language of the NPRM regarding that 
material.

Cost Impact

    There are approximately 110 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 21 airplanes of U.S. registry 
will be affected by this AD. The changes in this action add no 
additional economic burden. The current costs for this AD are repeated 
for the convenience of affected operators, as follows:
    It takes approximately 8 work hours per airplane to accomplish the 
actions currently required by AD 2003-11-15, at an average labor rate 
of $65 per work hour. Required parts are provided at no cost to the 
operator. Based on these figures, the cost impact of the actions 
currently required by AD 2003-11-15 is estimated to be $10,920, or $520 
per airplane.
    The cost impact figure discussed above 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 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.

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

0
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:

[[Page 74172]]

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. Section 39.13 is amended by removing amendment 39-13174 (68 FR 
33355, June 4, 2003), and by adding a new airworthiness directive (AD), 
amendment 39-13400, to read as follows:

2003-11-15 R1 McDonnell Douglas: Amendment 39-13400. Docket 2003-NM-
169-AD. Revises AD 2003-11-15, Amendment 39-13174.

    Applicability: All Model MD-90-30 airplanes, 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 (c) 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 ensure that the lanyards on the pressure relief door for the 
thrust reverser have adequate strength so that the door will not 
detach from the thrust reverser in the event that an engine bleed 
air duct bursts, which could result in the door striking and 
damaging the horizontal stabilizer, accomplish the following:

Replacement of Lanyards on the Thrust Reverser Pressure Relief Door

    (a) Within 18 months after the effective date of the AD, replace 
the lanyards on the pressure relief door for the thrust reverser 
with new, improved lanyards, and accomplish associated 
modifications, per the Accomplishment Instructions of Boeing Service 
Bulletin MD90-78-048, dated February 15, 2001. The associated 
modifications include removing the pressure relief door, modifying 
the pressure relief door (including replacing existing brackets with 
new brackets and re-identifying the door with a new part number), 
modifying the lower track beam (including removing terminals, 
replacing the aft quick-release pin with a new pin, and re-
identifying the beam with a new part number), modifying the heat 
shield on the lanyard assembly attach lugs, and re-installing the 
pressure relief door.

    Note 2: Boeing Service Bulletin MD90-78-048, dated February 15, 
2001, refers to International Aero Engines Service Bulletin V2500-
NAC-78-0184, dated February 16, 2001, for instructions on replacing 
the lanyards on the pressure relief door for the thrust reverser.

Parts Installation

    (b) After the effective date of this AD, no person may install a 
lanyard having part number (S700M1392A170) or (S700M1392A161) on the 
pressure relief door for the thrust reverser on any airplane.

Alternative Methods of Compliance

    (c) 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. 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 3: 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

    (d) 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

    (e) Unless otherwise specified in this AD, the actions shall be 
done in accordance with Boeing Service Bulletin MD90-78-048, dated 
February 15, 2001. This incorporation by reference was approved 
previously by the Director of the Federal Register as of July 9, 
2003 (68 FR 33355, June 4, 2003). Copies may be obtained from Boeing 
Commercial Aircraft Group, Long Beach Division, 3855 Lakewood 
Boulevard, Long Beach, California 90846, Attention: Data and Service 
Management, Dept. C1-L5A (D800-0024). 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, 3960 Paramount Boulevard, Lakewood, California; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

Effective Date

    (f) This amendment becomes effective on January 27, 2004.

    Issued in Renton, Washington, on December 12, 2003.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-31439 Filed 12-22-03; 8:45 am]
BILLING CODE 4910-13-P