[Federal Register Volume 69, Number 72 (Wednesday, April 14, 2004)]
[Rules and Regulations]
[Pages 19758-19759]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-8299]



[[Page 19758]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-212-AD; Amendment 39-13571; AD 2004-08-02]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model 717-200 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain McDonnell Douglas Model 717-200 airplanes, that 
requires a general visual inspection to detect corrosion of the left- 
and right-hand horizontal stabilizer hinge fitting bolts, barrel nuts, 
and the associated holes in the horizontal stabilizer structure, and to 
detect corrosion of the left- and right-hand elevator sector pinch 
bolts and associated holes, as applicable; and corrective actions, if 
necessary. This action is necessary to detect and correct corrosion of 
the left- and right-hand horizontal stabilizer hinge fitting bolts, 
barrel nuts, and associated holes in the horizontal stabilizer 
structure, and the left- and right-hand elevator sector pinch bolts and 
associated holes, which could lead to loss of a hinge fitting and 
reduced structural integrity of the horizontal stabilizer. This action 
is intended to address the identified unsafe condition.

DATES: Effective May 19, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 19, 2004.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplanes, Long Beach Division, 3855 
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and 
Service Management, Dept. C1-L5A (D800-0024). 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: Maureen Moreland, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5238; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain McDonnell Douglas Model 
717-200 airplanes was published in the Federal Register on November 26, 
2003 (68 FR 66382). That action proposed to require a general visual 
inspection to detect corrosion of the left- and right-hand horizontal 
stabilizer hinge fitting bolts, barrel nuts, and the associated holes 
in the horizontal stabilizer structure, and to detect corrosion of the 
left- and right-hand elevator sector pinch bolts and associated holes, 
as applicable; and corrective actions, if necessary.

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.

Cost Impact

    There are approximately 84 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 work hours vary according to the 
configuration group to which the affected airplane belongs.
    The following table shows the estimated cost impact for airplanes 
affected by this AD:

                                               Table--Cost Impact
----------------------------------------------------------------------------------------------------------------
                                                          Work hours per
              Airplane configuration group                   airplane       Labor rate per    Cost per airplane
                                                            (estimated)        work hour         (estimated)
----------------------------------------------------------------------------------------------------------------
1......................................................                61               $65               $3,965
2......................................................                57                65                3,705
----------------------------------------------------------------------------------------------------------------

    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. Manufacturer warranty remedies may be available 
for labor costs associated with this AD. As a result, the costs 
attributable to the AD may be less than stated above.

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.

[[Page 19759]]

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:

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 adding the following new airworthiness 
directive:

2004-08-02 McDonnell Douglas: Amendment 39-13571. Docket 2002-NM-
212-AD.

    Applicability: Model 717-200 airplanes, as listed in Boeing 
Service Bulletin 717-55-0003, dated June 18, 2002; certificated in 
any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct corrosion of the left- and right-hand 
horizontal stabilizer hinge fitting bolts, barrel nuts, and 
associated holes in the horizontal stabilizer structure, and the 
left- and right-hand elevator sector pinch bolts and associated 
holes, which could lead to loss of a hinge fitting and reduced 
structural integrity of the horizontal stabilizer; accomplish the 
following:

Service Bulletin References

    (a) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of Boeing Service Bulletin 717-55-0003, 
dated June 18, 2002.

Initial Inspection

    (b) Prior to the accumulation of 18,000 total flight cycles, or 
within 15 months after the effective date of this AD, whichever is 
later: Perform the general visual inspections specified in 
paragraphs (c) and (d) of this AD, as applicable, in accordance with 
the service bulletin.

    Note 1: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made from within 
touching distance unless otherwise specified. A mirror may be 
necessary to enhance visual access to all exposed surfaces in the 
inspection area. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or droplight and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

Horizontal Stabilizer Hinge Fitting Bolt Inspection

    (c) For Group 1 and Group 2 airplanes identified in paragraph 
1.A.1. of the service bulletin: Perform a general visual inspection 
of the left- and right-hand horizontal stabilizer hinge fitting 
bolts, barrel nuts, and the associated holes in the horizontal 
stabilizer for corrosion in accordance with the service bulletin.
    (1) If no corrosion is found, before further flight, install 
bolts and barrel nuts with applicable corrosion protection, in 
accordance with the service bulletin.
    (2) If any corrosion is found, before further flight, remove the 
corrosion and do the actions specified in paragraph (c)(2)(i) or 
(c)(2)(ii) of this AD, as applicable, in accordance with the service 
bulletin.
    (i) If corrosion rework is within tolerance limits, before 
further flight, perform the corrective actions in accordance with 
the service bulletin, as applicable.
    (ii) If corrosion rework exceeds the tolerance limits and the 
service bulletin specifies to contact Boeing for repair: Before 
further flight, repair in accordance with a method approved by the 
Manager, Los Angeles Aircraft Certification Office (ACO), FAA; or in 
accordance with data meeting the type certification basis of the 
airplane approved by a Boeing Company Designated Engineering 
Representative (DER) who has been authorized by the Manager, Los 
Angeles ACO, to make such findings. For a repair method to be 
approved, the approval must specifically reference this AD.

Elevator Sector Pinch Bolt Inspection

    (d) For Group 1 airplanes identified in paragraph 1.A.1. of the 
service bulletin: Perform a general visual inspection of the left- 
and right-hand elevator sector pinch bolts and associated holes for 
corrosion in accordance with the service bulletin.
    (1) If no corrosion is found, before further flight, install 
bolts and barrel nuts with applicable corrosion protection in 
accordance with the service bulletin.
    (2) If any corrosion is found, before further flight, remove the 
corrosion and do the actions specified in paragraph (d)(2)(i) or 
(d)(2)(ii) of this AD, as applicable, in accordance with the service 
bulletin.
    (i) If corrosion rework is within tolerance limits, before 
further flight, perform the corrective actions in accordance with 
the service bulletin, as applicable.
    (ii) If corrosion rework exceeds the tolerance limits and the 
service bulletin specifies to contact Boeing for repair: Before 
further flight, repair in accordance with a method approved by the 
Manager, Los Angeles ACO, FAA; or in accordance with data meeting 
the type certification basis of the airplane approved by a Boeing 
Company DER who has been authorized by the Manager, Los Angeles ACO, 
to make such findings. For a repair method to be approved, the 
approval must specifically reference this AD.

Alternative Methods of Compliance

    (e) In accordance with 14 CFR 39.19, the Manager, Los Angeles 
Aircraft Certification Office (ACO), FAA, is authorized to approve 
alternative methods of compliance (AMOCs) for this AD.

Incorporation by Reference

    (f) Unless otherwise specified in this AD, the actions shall be 
done in accordance with Boeing Service Bulletin 717-55-0003, dated 
June 18, 2002. This incorporation by reference was 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 Boeing Commercial 
Airplanes, 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

    (g) This amendment becomes effective on May 19, 2004.

    Issued in Renton, Washington, on April 6, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-8299 Filed 4-13-04; 8:45 am]
BILLING CODE 4910-13-P