[Federal Register Volume 69, Number 124 (Tuesday, June 29, 2004)]
[Rules and Regulations]
[Pages 38824-38826]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-14568]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-126-AD; Amendment 39-13697; AD 2004-13-15]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-400 and -400D Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Boeing Model 747-400 and -400D series airplanes, 
that requires an inspection to detect missing fasteners in the section 
42 skin and internal doubler at the cutout for the ground exhaust valve 
of the electrical equipment; modification and rework of the doubler; 
repetitive inspections of the skin for cracks; and corrective actions 
if necessary; as applicable. This action is necessary to detect and 
correct fatigue cracks in the section 42 skin at the cutout for the 
ground exhaust valve of the electrical equipment, which could result in 
rapid decompression of the airplane. This action is intended to address 
the identified unsafe condition.

DATES: Effective August 3, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 3, 2004.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the Federal 
Aviation

[[Page 38825]]

Administration (FAA), Transport Airplane Directorate, Rules Docket, 
1601 Lind Avenue, SW., Renton, Washington; or at the National Archives 
and Records Administration (NARA). For information on the availability 
of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

FOR FURTHER INFORMATION CONTACT: Candice Gerretsen, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6428; fax (425) 917-6590.

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 Boeing Model 747-400 and -
400D series airplanes was published in the Federal Register on April 1, 
2004 (69 FR 17073). That action proposed to require an inspection to 
detect missing fasteners in the section 42 skin and internal doubler at 
the cutout for the ground exhaust valve of the electrical equipment; 
modification and rework of the doubler; repetitive inspections of the 
skin for cracks; and corrective actions if necessary; as applicable.

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 142 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 22 airplanes of U.S. registry 
will be affected by this AD.
    For Group 1 airplanes listed in Boeing Alert Service Bulletin 747-
53A2340, it will take approximately 1 work hour per airplane to 
accomplish the required inspection (part 1), at an average labor rate 
of $65 per work hour. Based on these figures, the cost impact of this 
inspection required by this AD on U.S. operators is estimated to be $65 
per airplane.
    For Groups 1 and 2 airplanes listed in Boeing Alert Service 
Bulletin 747-53A2340, it will take approximately 40 work hours per 
airplane to accomplish the required modification and rework (part 2), 
at an average labor rate of $65 per work hour. Based on these figures, 
the cost impact of this modification and rework required by this AD on 
U.S. operators is estimated to be $2,600 per airplane.
    For Groups 1 through 4 airplanes listed in Boeing Alert Service 
Bulletin 747-53A2340, it will take approximately 1 work hours per 
airplane to accomplish the required inspection (part 3), at an average 
labor rate of $65 per work hour. Based on these figures, the cost 
impact of this inspection required by this AD on U.S. operators is 
estimated to be $65 per airplane, per inspection cycle.
    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:

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:

2004-13-15 Boeing: Amendment 39-13697. Docket 2003-NM-126-AD.

    Applicability: Model 747-400 and 400D series airplanes, as 
listed in paragraph 1.A., ``Effectivity,'' of Boeing Alert Service 
Bulletin 747-53A2340, Revision 2, dated April 24, 2003; certificated 
in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct fatigue cracks in the section 42 skin at 
the cutout for the ground exhaust valve of the electrical equipment, 
which could result in rapid decompression of the airplane, 
accomplish the following:

Part 1--Fastener Inspection and Corrective Actions if Necessary

    (a) For Group 1 airplanes listed in Boeing Alert Service 
Bulletin 747-53A2340, Revision 2, dated April 24, 2003: Within 250 
flight cycles or 4 months after the effective date of this AD, 
whichever occurs later, do a general visual inspection to detect 
missing fasteners in the section 42 skin and internal doubler at the 
cutout for the ground exhaust valve of the electrical equipment, per 
part 1 of the Accomplishment Instructions of the service bulletin.
    (1) If all fasteners are installed, do the actions specified in 
paragraph (b) of this AD at the indicated time.
    (2) If any fastener is missing, before further flight, 
accomplish all applicable corrective actions (i.e., performing an 
open hole high frequency (HFEC) inspection for cracks and any 
applicable repair, oversizing and drilling of holes, and 
installation of fasteners), in accordance with part 1 of the 
Accomplishment Instructions of the service bulletin, except as 
required by paragraph (f) of this AD.

Part 2--Modification and Rework

    (b) For Group 1 and Group 2 airplanes listed in Boeing Alert 
Service Bulletin 747-53A2340, Revision 2, dated April 24, 2003: 
Before the accumulation of 6,000 total flight cycles, or within 
1,500 flight cycles or 24 months after the effective date of this 
AD, whichever occurs later, modify and rework the internal doubler 
(i.e., performing an open hole HFEC inspection for cracks and any 
applicable repair, oversizing and drilling of holes, and 
installation of fasteners) by accomplishing all actions specified in 
part 2

[[Page 38826]]

of the Accomplishment Instructions of the service bulletin. Do the 
actions per the service bulletin, except as required by paragraph 
(f) of this AD. Any applicable repair must be accomplished before 
further flight.

Part 3--Repetitive Inspections and Repair if Necessary

    (c) At the applicable time specified in paragraph (c)(1) or 
(c)(2) of this AD, do an external HFEC inspection of the skin for 
cracks per part 3 of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2340, Revision 2, dated April 24, 2003.
    (1) For Group 1 and Group 2 airplanes listed in the service 
bulletin: Within 10,000 flight cycles after accomplishing the 
actions required by paragraph (b) of this AD, or within 1,500 flight 
cycles or 24 months after the effective date of this AD, whichever 
occurs later.
    (2) For Group 3 and Group 4 airplanes listed in the service 
bulletin: Before the accumulation of 15,000 total flight cycles, or 
within 1,500 flight cycles or 24 months after the effective date of 
this AD, whichever occurs later.
    (d) If no crack is detected during the external HFEC inspection 
required by paragraph (c) of this AD, repeat the external HFEC 
inspection thereafter at intervals not to exceed 5,000 flight 
cycles.
    (e) If any crack is detected during the external HFEC inspection 
required by paragraph (c) of this AD, before further flight, repair 
per part 3 of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2340, Revision 2, dated April 24, 2003, 
except as required by paragraph (f) of this AD. Repeat the external 
HFEC inspection in the unrepaired areas thereafter at intervals not 
to exceed 5,000 flight cycles.

Exception to Service Bulletin Actions

    (f) If any discrepancy is found during any inspection required 
by this AD, and the bulletin specifies to contact Boeing for an 
alternate repair: Before further flight, repair per a method 
approved by the Manager, Seattle Aircraft Certification Office 
(ACO), FAA; or per data meeting the type certification basis of the 
airplane approved by a Boeing Company Designated Engineering 
Representative who has been authorized by the Manager, Seattle ACO, 
to make such findings. For a repair method to be approved, the 
approval must specifically reference this AD.

Credit for Previous Revisions of Service Bulletins

    (g) Actions accomplished before the effective date of this AD 
per Boeing Alert Service Bulletin 747-53A2340, original issue, dated 
August 1, 1991; or Revision 1, dated October 31, 1991, are 
acceptable for compliance with the requirements of this AD.

Alternative Methods of Compliance

    (h)(1) In accordance with 14 CFR 39.19, the Manager, Seattle 
ACO, FAA, is authorized to approve alternative methods of compliance 
(AMOCs) for this AD.
    (2) An AMOC that provides an acceptable level of safety may be 
used for any inspection or repair required by this AD, if it is 
approved by a Boeing Company Designated Engineering Representative 
who has been authorized by the Manager, Seattle ACO, to make such 
findings. For an inspection or repair method to be approved, the 
approval must specifically reference this AD.

Incorporation by Reference

    (i) Unless otherwise specified in this AD, the actions shall be 
done in accordance with Boeing Alert Service Bulletin 747-53A2340, 
Revision 2, dated April 24, 2003. 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, P.O. Box 3707, Seattle, Washington 
98124-2207. Copies may be inspected at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call (202) 741-6030, 
or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

Effective Date

    (j) This amendment becomes effective on August 3, 2004.


    Issued in Renton, Washington, on June 17, 2004.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-14568 Filed 6-28-04; 8:45 am]
BILLING CODE 4910-13-P