Airworthiness Directives; Boeing Model 727 and 727C Series Airplanes

[Federal Register Volume 65, Number 84 (Monday, May 1, 2000)]
[Rules and Regulations]
[Pages 25278-25279]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-10287]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-293-AD; Amendment 39-11705; AD 2000-08-19]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727 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 and 727C series airplanes, that 
requires one-time inspections of the exterior body skin located at the 
forward corners of the mid-galley door hinge cutouts to detect 
cracking, and corrective actions, if necessary. This AD also requires 
modification of the body skin of the mid-galley door hinge cutouts. 
This amendment is prompted by a report indicating that, during fatigue 
testing on a Boeing Model 727 series airplane, a crack was found in the 
body skin at the lower forward corners of the mid-galley door hinge 
cutouts due to cabin pressurization cycles. The actions specified by 
this AD are intended to prevent such fatigue cracking of the body skin, 
which could result in reduced structural integrity of the fuselage and 
consequent loss of cabin pressurization.

DATES: Effective June 5, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 5, 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: Walter Sippel, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Transport Airplane Directorate, Seattle 
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 227-2774; 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 727 and 727C 
series airplanes was published in the Federal Register on November 22, 
1999 (64 FR 63753). That action proposed to require one-time 
inspections of the exterior body skin located at the forward corners of 
the mid-galley door hinge cutouts to detect cracking; corrective 
actions, if necessary; and modification of the body skin of the mid-
galley door hinge cutouts.

Comments

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

Airplanes Not Affected

    On behalf of two of its members, the Air Transport Association of 
America (ATA) comments that no airplanes operated by those two members 
are affected by this proposal. The ATA makes no further comment or 
request.

Request to Remove Airplanes From Applicability

    One commenter, the manufacturer, requests that the FAA revise the 
applicability statement of the proposed AD to remove two airplanes. The 
commenter states that, according to its records, the airplanes having 
line numbers 153 and 339 were determined to be irreparable on August 8, 
1965, and February 16, 1968, respectively.
    The FAA does not concur with the commenter's request. Though the 
commenter states that the airplanes were determined to be irreparable, 
the FAA considers it possible that the subject airplanes could be 
repaired by an entity other than the manufacturer. Should one of these 
airplanes be repaired and added to the U.S. Register in the future, the 
FAA finds that, to ensure safe operation, the airplane must be 
inspected, repaired, and modified, as applicable, in accordance with 
the requirements of this AD. No change to the final rule is necessary.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Cost Impact

    There are approximately 1,516 Boeing Model 727 and 727C series 
airplanes of the affected design in the worldwide fleet. The FAA 
estimates that 3 airplanes of U.S. registry will be affected by this 
AD.
    The FAA estimates that it will take approximately 1 work hour per 
airplane to accomplish the required inspections of the body skin at the 
corners of the mid-galley door hinge cutouts, and that the average 
labor rate is $60 per work hour. Based on these figures, the cost 
impact of the inspections required by this AD on U.S. operators is 
estimated to be $180, or $60 per airplane.
    The FAA also estimates that it will take approximately 28 work 
hours per airplane to accomplish the repair and modification, and that 
the average labor rate is $60 per work hour. Required parts will cost 
approximately $1,023 per

[[Page 25279]]

airplane. Based on these figures, the cost impact of the repair and 
modification required by this AD on U.S. operators is estimated to be 
$8,109, or $2,703 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.

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 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:

2000-08-19 Boeing: Amendment 39-11705. Docket 98-NM-293-AD.

    Applicability: Model 727 and 727C series airplanes, line numbers 
153, 290, and 339 inclusive; 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 (b) 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 body skin at the forward 
corners of the mid-galley door hinge cutouts, which could result in 
reduced structural integrity of the fuselage and consequent loss of 
cabin pressurization, accomplish the following:

One-Time Inspections

    (a) Prior to the accumulation of 60,000 total flight cycles, or 
within 3,000 flight cycles after the effective date of this AD, 
whichever occurs later, perform a one-time detailed visual 
inspection and a high frequency eddy current inspection of the 
exterior body skin located adjacent to the forward corners of the 
mid-galley door hinge cutouts for cracking in accordance with Boeing 
Service Bulletin 727-53-0054, Revision 1, dated November 16, 1989.

    Note 2: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive 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 an intensity 
deemed appropriate by the inspector. Inspection aids such as 
mirrors, magnifying lenses, etc. may be used. Surface cleaning and 
elaborate access procedures may be required.''

Repairs and Modification

    (1) If no cracking is found during any inspection, prior to 
further flight, modify the body skin at the forward corners of the 
mid-galley door hinge cutouts, in accordance with Boeing Service 
Bulletin 727-53-0054, Revision 1, dated November 16, 1989. No 
further action is required by this AD.
    (2) If any cracking is found during any inspection, prior to 
further flight, accomplish the requirements of either paragraph 
(a)(2)(i) or (a)(2)(ii) of this AD, as applicable.
    (i) If any crack is less than or equal to 1.00 inch, accomplish 
the repair and modification in accordance with Boeing Service 
Bulletin 727-53-0054, Revision 1, dated November 16, 1989. No 
further action is required by this AD.
    (ii) If any crack is greater than 1.00 inch, accomplish the 
repair and modification in accordance with a method approved by the 
Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport 
Airplane Directorate; or in accordance with 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 by the Manager, Seattle ACO, as required by this 
paragraph, the Manager's approval letter must specifically reference 
this AD. No further action is required by this AD.

    Note 3: Accomplishment of the actions required by AD 90-06-09, 
amendment 39-6488, is considered acceptable for compliance with this 
AD.

Alternative Method of Compliance

    (b) 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, FAA, Transport 
Airplane Directorate. 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 4: 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

    (c) 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

    (d) Except as provided by paragraph (a)(2)(ii) of this AD, the 
actions shall be done in accordance with Boeing Service Bulletin 
727-53-0054, Revision 1, dated November 16, 1989. 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

    (e) This amendment becomes effective on June 5, 2000.

    Issued in Renton, Washington, on April 19, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-10287 Filed 4-28-00; 8:45 am]
BILLING CODE 4910-13-U

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