Airworthiness Directives; Boeing Model 777 Series Airplanes

[Federal Register Volume 65, Number 81 (Wednesday, April 26, 2000)]
[Rules and Regulations]
[Pages 24383-24384]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-10160]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-346-AD; Amendment 39-11701; AD 2000-08-15]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 777 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 777 series airplanes, that requires a one-
time inspection to detect cracking of the fastener holes common to the 
upper wing skins and trailing edge panels of both wings, and corrective 
actions, if necessary. This amendment also requires coldwork of the 
fastener holes and installation of new or serviceable fasteners. This 
amendment is prompted by a report indicating that fatigue cracks have 
been found in the upper wing skin of both wings. The actions specified 
by this AD are intended to prevent fatigue cracking of the upper wing 
skin, which could result in reduced structural integrity of the wing.

DATES: Effective May 31, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 31, 2000.

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: Stan Wood, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Transport Airplane Directorate, Seattle 
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 227-2772; 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 777 series 
airplanes was published in the Federal Register on January 4, 2000 (65 
FR 250). That action proposed to require a one-time inspection to 
detect cracking of the fastener holes common to the upper wing skins 
and trailing edge panels of both wings, and corrective actions, if 
necessary. That action also proposed to require coldwork of the 
fastener holes and installation of new or serviceable fasteners.

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 82 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 33 airplanes of U.S. registry 
will be affected by this AD, that it will take approximately 13 work 
hours per airplane to accomplish the required actions, and that the 
average labor rate is $60 per work hour. Required parts will cost 
approximately $216 per airplane. Based on these figures, the cost 
impact of the AD on U.S. operators is estimated to be $32,868, or $996 
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.

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

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation

[[Page 24384]]

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:

2000-08-15  Boeing: Amendment 39-11701. Docket 99-NM-346-AD.

    Applicability: Model 777 series airplanes having line numbers 1 
through 119 inclusive, except line numbers 94, 102, 104, and 118; 
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 prevent fatigue cracking of the upper wing skin, which could 
result in reduced structural integrity of the wing, accomplish the 
following:

Eddy Current Inspection of Fastener Holes

    (a) Prior to the accumulation of 16,000 total flight cycles or 
40,000 total flight hours, whichever occurs earlier, perform a one-
time eddy current inspection to detect cracking of the fastener 
holes common to the upper wing skins and trailing edge panels of 
both wings, in accordance with Boeing Alert Service Bulletin 777-
57A0022, dated August 26, 1999.

Rework and Re-Inspection of Fastener Hole

    (b) If any cracking is detected during the inspection required 
by paragraph (a) of this AD, prior to further flight, oversize the 
fastener hole and perform additional eddy current inspections to 
detect cracking of the fastener holes until all cracking is no 
longer detectable by means of eddy current inspection. Perform the 
actions in accordance with Boeing Alert Service Bulletin 777-
57A0022, dated August 26, 1999. Prior to further flight, oversize 
the fastener hole an additional 1/32-inch minimum and measure the 
starting hole diameter and edge margin of the fastener hole, in 
accordance with the alert service bulletin.
    (1) If the fastener hole diameter or the edge margin of any 
fastener hole is not within the limits specified in the alert 
service bulletin, prior to further flight, repair in accordance with 
a method approved by the Manager, Seattle Aircraft Certification 
Office (ACO), FAA, Transport Airplane Directorate, or a Boeing 
Company Designated Engineering Representative who has been 
authorized by the FAA to make such findings. For a repair method to 
be approved by the Manager, Seattle ACO, as required by this 
paragraph, the Manager's approval letter must specifically reference 
this AD.
    (2) If the fastener hole diameter and edge margin of all the 
fastener holes are within the limits specified in the alert service 
bulletin, prior to further flight, accomplish the requirements of 
paragraph (c) of this AD.

Coldwork of Fastener Holes

    (c) If no cracking is detected during the eddy current 
inspection required by paragraph (a), or the fastener hole diameter 
and edge margin of all the fastener holes are within the limits 
required by paragraph (b) of this AD, prior to further flight, 
coldwork the fastener holes and install new or serviceable 
fasteners, in accordance with Boeing Alert Service Bulletin 777-
57A0022, dated August 26, 1999.

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 2:
    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 paragraph (b)(1) of this AD, the 
actions shall be done in accordance with Boeing Alert Service 
Bulletin 777-57A0022, dated August 26, 1999. 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.
    (g) This amendment becomes effective on May 31, 2000.

    Issued in Renton, Washington, on April 18, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-10160 Filed 4-25-00; 8:45 am]
BILLING CODE 4910-13-P

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