[Federal Register Volume 67, Number 232 (Tuesday, December 3, 2002)]
[Rules and Regulations]
[Pages 71812-71814]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-30343]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-17-AD; Amendment 39-12968; AD 2002-24-03]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747 Series Airplanes 
Powered by General Electric (GE) CF6-80C2 Series Engines

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 747 series airplanes powered by GE 
CF6-80C2 series engines, that requires repetitive inspections and 
torque checks to find discrepancies of the fasteners that attach the 
diagonal brace fittings of the lower spar to the inboard engine struts, 
and modification of the fasteners if discrepancies are found. This 
amendment also requires eventual modification of all the fasteners, 
which ends the repetitive inspections and checks. The actions specified 
by this AD are intended to find and fix discrepant fasteners of the 
diagonal brace fittings, which could result in reduced structural 
integrity of the diagonal brace-to-strut attachment, and possible 
separation of the strut and engine from the airplane. This action is 
intended to address the identified unsafe condition.

DATES: Effective January 7, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 7, 2003.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplane Group, 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: Tamara Anderson, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2771; fax (425) 227-1181.

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 series 
airplanes powered by General Electric CF6-80C2 series engines was 
published in the Federal Register on August 30, 2002 (67 FR 55739). 
That action proposed to require repetitive inspections and torque 
checks to find discrepancies of the fasteners that attach the diagonal 
brace fittings of the lower spar to the inboard engine struts, and 
modification of the fasteners if discrepancies are found. That action 
also proposed to require eventual modification of all the fasteners, 
which would end the repetitive inspections and checks.

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.

Explanation of Editorial Change

    We have changed the service bulletin citation throughout this final 
rule to exclude the Evaluation Form. (The form is intended to be 
completed by operators and submitted to the manufacturer to provide 
input on the quality of the service bulletin; however, this AD does not 
include such a requirement.)

Cost Impact

    There are approximately 237 airplanes of the affected design in the 
worldwide fleet. We estimate that 14 airplanes of U.S. registry will be 
affected by this AD.
    It will take approximately 5 work hours per airplane to accomplish 
the inspection and torque check at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of the required 
actions on U.S. operators is estimated to be $4,200, or $300 per 
airplane, per inspection/check cycle.
    It will take approximately 76 work hours per airplane to accomplish 
the terminating action at an average labor rate of $60 per work hour. 
Required parts will cost approximately $4,268 per airplane. Based on 
these figures, the cost impact of this required action on U.S. 
operators is estimated to be $123,592, or $8,828 per airplane.
    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

[[Page 71813]]

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 adding the following new 
airworthiness directive:

2002-24-03 Boeing: Amendment 39-12968. Docket 2001-NM-17-AD.
    Applicability: Model 747-200B, -300, -400, -400D, and -400F 
series airplanes powered by General Electric CF6-80C2 series 
engines, as listed in Boeing Alert Service Bulletin 747-54A2207, 
dated November 16, 2000, 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 (d) 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 find and fix discrepant fasteners of the diagonal brace 
fittings, which could result in reduced structural integrity of the 
diagonal brace-to-strut attachment, and possible separation of the 
strut and engine from the airplane, accomplish the following:

Repetitive Inspections and Torque Checks/Corrective Action

    (a) Do a detailed inspection and torque check to find 
discrepancies of the fasteners (e.g., loose, fractured, or missing 
fastener heads) that attach the diagonal brace fittings of the lower 
spar to the inboard engine struts, at the applicable time specified 
in paragraph (a)(1) or (a)(2) of this AD, per Boeing Alert Service 
Bulletin 747-54A2207, dated November 16, 2000, excluding Evaluation 
Form. Repeat the inspection and check after that every 8,000 flight 
hours or 24 months, whichever is first.

    Note 2: For the purposes of this AD, a detailed 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.''

    (1) For airplanes that have not been modified as required by AD 
95-13-06, amendment 39-9286 (all Group 2 airplanes): Before the 
accumulation of 6,000 total flight cycles or within 24 months after 
the effective date of this AD, whichever is later.
    (2) For airplanes that have been modified as required by AD 95-
13-06 (all Group 1 airplanes): Before the accumulation of 6,000 
total flight cycles after doing the modification or within 24 months 
after the effective date of this AD, whichever is later.
    (b) If no discrepancy is found during any inspection/check 
required by paragraph (a) of this AD, repeat the inspection/check at 
the time specified in paragraph (a) of this AD until the terminating 
action specified in paragraph (c) of this AD is done. If any 
discrepancy is found, do the applicable actions specified in 
paragraph (b)(1) or (b)(2) of this AD.
    (1) If any discrepancy is found in the area that connects the 
diagonal brace fitting to the aft bulkhead, 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 (DER) who has been authorized 
by the Manager, Seattle ACO, to make such findings. For a repair 
method to be approved, as required by this paragraph, the approval 
must specifically reference this AD.
    (2) If any discrepancy is found in any area other than that 
specified in paragraph (b)(1) of this AD, before further flight, do 
the terminating action specified in paragraph (c) of this AD.

Terminating Action

    (c) Except as provided by paragraph (b)(2) of this AD, within 72 
months after the effective date of this AD: Do the modification 
(including doing a high frequency eddy current (HFEC) inspection, 
oversizing the fastener holes, and installing new fasteners) as 
specified in and per Figure 3 of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-54A2207, dated November 16, 2000, 
excluding Evaluation Form. If any cracking is found during the HFEC 
inspection and the service bulletin specifies contacting Boeing for 
repair procedures, before further flight, repair per a method 
approved by the Manager, Seattle ACO; or per data meeting the type 
certification basis of the airplane approved by a Boeing Company DER 
who has been authorized by the Manager, Seattle ACO, to make such 
findings. For a repair method to be approved, as required by this 
paragraph, the approval must specifically reference this AD. 
Accomplishment of the actions specified in this paragraph ends the 
repetitive inspections and checks.

Alternative Methods of Compliance

    (d) 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, Seattle ACO. Operators shall submit 
their requests through an appropriate FAA Principal Maintenance 
Inspector, who may add comments and then send it to the Manager, 
Seattle ACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (e) 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

    (f) Except as provided by paragraphs (b)(1) and (c) of this AD, 
the actions shall be done in accordance with Boeing Alert Service 
Bulletin 747-54A2207, dated November 16, 2000, excluding Evaluation 
Form. 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 Airplane 
Group, 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

    (g) This amendment becomes effective on January 7, 2003.


[[Page 71814]]


    Issued in Renton, Washington, on November 20, 2002.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-30343 Filed 12-2-02; 8:45 am]
BILLING CODE 4910-13-P