[Federal Register Volume 69, Number 32 (Wednesday, February 18, 2004)]
[Rules and Regulations]
[Pages 7550-7551]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-3130]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-191-AD; Amendment 39-13475; AD 2004-03-31]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727, 727-100C, 727-200F, 
and 727C Series 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 Boeing Model 727, 727-100C, 727-200F, and 727C 
series airplanes, that requires repetitive open-hole high frequency 
eddy current inspections for cracks in the fuselage skin, strap 
(bearstrap), and doubler at the forward and aft hinge fittings for the 
main deck cargo door, and repair of any cracks found. This action is 
necessary to detect and correct such cracks, which could reach critical 
crack length and result in rapid decompression of the airplane. This 
action is intended to address the identified unsafe condition.

DATES: Effective March 24, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 24, 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 Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437; 
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 727, 727-
100C, 727-200F, and 727C series airplanes was published in the Federal 
Register on November 18, 2003 (68 FR 64998). That action proposed to 
require repetitive open-hole high frequency eddy current inspections 
for cracks in the fuselage skin, strap (bearstrap), and doubler at the 
forward and aft hinge fittings for the main deck cargo door, and repair 
of any cracks found.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comment received.

Request To Allow Designated Engineering Representative (DER) Approval

    The commenter, the manufacturer, requests that paragraph (b) of the 
proposed AD be revised to alternatively allow DERs to approve 
alternative methods of compliance (AMOC) for the actions specified in 
paragraph (a) of the proposed AD.
    The FAA agrees. The option to allow DER approval of AMOCs was 
inadvertently omitted from paragraph (b) of the proposed AD. Therefore, 
we have revised paragraph (b) of this final rule to include that 
provision.

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 with the change previously 
described. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Interim Action

    We consider this AD to be interim action. If final action is later 
identified, we may consider further rulemaking then.

Cost Impact

    There are approximately 195 airplanes of the affected design in the 
worldwide fleet. We estimate that 133 airplanes of U.S. registry will 
be affected by this AD. We provide the following cost estimates to 
comply with this AD, per inspection cycle:

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                                                                              Hourly                   Cost per
                            Group                              Work hours   labor rate     Parts       airplane
----------------------------------------------------------------------------------------------------------------
1...........................................................            7          $65           $0         $455
2...........................................................            8          $65           $0         $520
3...........................................................            8          $65           $0         $520
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[[Page 7551]]

    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.

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:

2004-03-31 Boeing: Amendment 39-13475. Docket 2003-NM-191-AD.

    Applicability: Model 727, 727-100C, 727-200F, and 727C series 
airplanes, certificated in any category, as listed in Boeing Alert 
Service Bulletin 727-53A0226, dated September 11, 2003.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct fatigue cracks in the fuselage skin, strap 
(bearstrap), or doubler at the forward and aft hinge fittings for 
the main deck cargo door, which could reach critical crack length 
and result in rapid decompression of the airplane, accomplish the 
following:

Inspection

    (a) Perform an open-hole high frequency eddy current inspection 
for cracks in the fuselage skin, strap (bearstrap), and doubler at 
the forward and aft hinge fittings for the main deck cargo door. Do 
the inspection at the applicable initial compliance time listed in 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
727-53A0226, dated September 11, 2003; except, where the service 
bulletin specifies a compliance time after the service bulletin 
date, this AD requires compliance within the specified compliance 
time after the effective date of this AD. Perform the inspection in 
accordance with the Accomplishment Instructions of the service 
bulletin.
    (1) If no crack is found: Repeat the inspection within the 
interval listed in paragraph 1.E., ``Compliance,'' of the service 
bulletin.
    (2) If any crack is found: Repair it before further flight in 
accordance with 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 (DER) who has been authorized 
by the Manager, Seattle ACO, to make such findings. For a repair 
method to be approved, the approval must specifically refer to this 
AD. Within 12 months following a repair, implement an inspection 
program for the repair into the 727 maintenance program in 
accordance with a method and compliance times approved by the 
Manager, Seattle ACO; or per data meeting 14 CFR 25.571 (Amendment 
25-54 or later) approved by a Boeing Company DER who has been 
authorized by the Manager, Seattle ACO, to make such findings.

Alternative Methods of Compliance

    (b)(1) In accordance with 14 CFR 39.19, the Manager, Seattle 
Aircraft Certification Office, FAA, is authorized to approve 
alternative methods of compliance for this AD.
    (2) An AMOC that provides an acceptable level of safety may be 
used for the requirements of paragraph (a) of this AD, if it is 
approved by a Boeing Company DER who has been authorized by the 
Manager, Seattle Aircraft Certification Office, to make such 
findings.

Incorporation by Reference

    (c) Unless otherwise specified by this AD, the actions must be 
done in accordance with Boeing Alert Service Bulletin 727-53A0226, 
dated September 11, 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 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

Effective Date

    (d) This amendment becomes effective on March 24, 2004.

    Issued in Renton, Washington, on February 5, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-3130 Filed 2-17-04; 8:45 am]
BILLING CODE 4910-13-U